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    Wyświetlanie 1-62 z 62
    Tytuł:
    Modeling and analysis of jet engine with cooling turbine
    Autorzy:
    Jakubowski, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/247838.pdf
    Data publikacji:
    2012
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    modelling of jet engine
    modelling of jet engine with cooling turbine
    Opis:
    The problems of the turbojet engines with a cooling turbine modelling are discussed in the paper. The cooling systems of the contemporary jet engines are briefly described in the first part of the paper. Than the models of various turbine, cooling systems are presented and discussed. The main scope of the paper is the turbine cooling system consisted of internal convection cooling and external film cooling of turbine blades. This cooling system is commonly used in contemporary military and civil turbojet engines. The model of the internal-external cooling turbine incorporated in the overall jet engine model is presented and discussed. Some simplifying assumptions are discussed. Then the results of the jet engine calculation taking into account the proposed model are presented in the tables. The results are compared with results obtained by simple model of the jet engine with cooling turbine. The simple model is commonly applied for 1D turbojet engine analysis. Based on this analysis, some aspects of the turbojet engine calculation with reference to different models applied for description of the turbine cooling process are presented and discussed. The analysis allowed formulating some conclusions, which are presented in the final part of the paper. One of them is that proposed model of cooling turbine allows to calculate of coolant mass flow, while the simple models of cooling turbine require the assumption of coolant mass. By this way the calculation results accuracy by the use of simple model, strictly depend on the proper assumption of coolant mass flow.
    Źródło:
    Journal of KONES; 2012, 19, 2; 235-243
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Preliminary analysis of two combustors turbofan engine
    Autorzy:
    Jakubowski, R.
    Orkisz, M
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/241925.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    turbofan engine
    Opis:
    The problems of turbofan engines development is briefly discussed in the beginning. Next the conception of turbofan engine with two combustors is presented, and an engine thermodynamic cycle is analysed. The proposed engine it is a modification of the contemporary turbofan engine by addition of another combustor. First one is classical combustor located between high pressure compressor and turbine. Second one is located between high pressure turbine and low pressure turbine. This conception allows to lower the high pressure turbine inlet temperature. The second combustor increases energy of gasses inflow the low pressure turbine to the sufficient level for fan drive. The results of numerical analysis are used to show performance of the proposed engine and to present their advantages with compare to the classical turbofan engine construction. Then some other positive aspects of two combustors engine are discussed. It refers to possibilities of pollution emission reduction and overhauling period increasing and engine life time extension. On the other hand some aspects of engine hot elements (turbine) production simplification and cost reduction is analysed. In the next chapter the problems of the proposed engine technical realization are discussed. The summary and conclusions are presented in the last part of article.
    Źródło:
    Journal of KONES; 2013, 20, 2; 175-180
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Comparison of the results of mathematical modeling of a GTM 120 miniature turbine jet engine with the research results
    Autorzy:
    Chachurski, R.
    Trzeciak, A.
    Jędrowiak, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/133071.pdf
    Data publikacji:
    2018
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    miniature jet engine
    jet engine
    miniaturowy silnik odrzutowy
    silnik odrzutowy
    Opis:
    The paper presents gas-dynamic calculations of a GTM 120 miniature turbine jet engine. The engine performance parameters have been determined and then validated with theory contained in literature as well as the results of research carried out on a laboratory test stand.
    Źródło:
    Combustion Engines; 2018, 57, 2; 30-33
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Diagnostics and analysis of jet engine malfunctions
    Autorzy:
    Rojewski, A.
    Bartoszewicz, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/242847.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    aircraft
    diagnostics
    safety
    Opis:
    The article describes emergency situations occurring in the propulsion system of an aircraft with the jet engine used in Poland on planes such as MiG-29 or F-16. The article also presents statistics of polish aircrafts damage over the years. Due to the technological progress of turbine engines used in fighter aircraft, the authors decided to discuss the issue of monitoring emergency states in this study. In particular, efforts have been made to ensure that damage to the aircraft engine can be prevented by monitoring its operation with the equipment available on the aircraft. Counteracting phenomena that occur in the jet engine can lead to permanent damage; can lead to an increase in the safety of the pilot and the local population, but also to a reduction of costs. The authors also decided to se the threats that occur during take-off and landing, and the flight when they land outside the plane. Jet engines are almost reliable and most common cause of engine damages as the analysis shows are foreign bodies, particularly dangerous for a turbine engine on or near the runway, as well as birds, which provides to mechanical damage of engine. Securing the airport against foreign objects on the runway is one of the most important tasks of ground staff.
    Źródło:
    Journal of KONES; 2018, 25, 2; 313-318
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Technological innovations in transport industry
    Autorzy:
    Zelenov, N.
    Powiązania:
    https://bibliotekanauki.pl/articles/409332.pdf
    Data publikacji:
    2012
    Wydawca:
    Politechnika Poznańska. Wydawnictwo Politechniki Poznańskiej
    Tematy:
    jet engine invention
    containerization
    tanker shipments
    Opis:
    Current situation stipulates growing requirements to the efficiency of economic subjects' performance. Big potential in this direction lies in the rationalization of logistical functions of organization, like: transportation, warehousing, interfunctional and interorganizational coordination, etc. One of the possible ways to rationalize firms' performance, without any doubt, is industry leaders' best practices application. However, to switch from the role of the follower to the leader it is essential for the organization to foresee future trends, including the field of effective flow management (logistics). Logistical technologies development was considered as an object of current paper: its main trends analysis and description of technological innovations that have resulted in decreasing of logistical costs in the goods shop cost in the last few decades were investigated. Also author has made a try to perform qualimetric analysis of the logistics technologies under consideration, i.e. to investigate dynamics of characterizing features of the analyzed object with the potential possibility to use these parameters for forecasting of future development trends. Problems of effective operation of two transport types (air and marine) and of several variants of transport-logistical delivery schemes (combined, container, tanker) were covered in the paper, inter alia following technological innovations were analyzed: jet engine invention, containerization and tanker shipments.
    Źródło:
    Research in Logistics & Production; 2012, 2, 4; 345-352
    2083-4942
    2083-4950
    Pojawia się w:
    Research in Logistics & Production
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Two-combustor turbofan engine performance analysis
    Autorzy:
    Jakubowski, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/241903.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    turbofan engine
    engine performance
    airplane engine development
    Opis:
    A conception of a two-combustor turbofan engine is the main scope of this paper. At the beginning, the problems of turbofan engines development are briefly discussed as a background of this work. In this part the turbofan engines innovation activities are presented. It is mentioned the engine’s innovations consists of many aspects but some important ones are: lowering of production operation cost, maintenance, reduction of noise and exhaust gases emission while engine reliability should stay on the same level or event increase. Next, the conception of turbofan engine with two combustors is presented in this context. Some positive aspects for environment, production and maintenance of such engine are discussed. Then the thermodynamic cycle of two-combustor engine is presented and analysed. On this basis, the engine numerical model is prepared. Next, some information about the model simplifications and calculations done to determine performance of the engine is presented. Then the results of the simulation calculations of the engine performance are presented and discussed. The relationship of engine thrust and specific fuel consumption vs. engine flight conditions are shown. Based on the results there were discussed the advantages and disadvantages of two combustors engine as an airplane propulsion are specified. The conclusions are formulated and presented in the last part of the paper.
    Źródło:
    Journal of KONES; 2014, 21, 3; 141-148
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Performance and emission characteristic of miniature turbojet engine FED Jet A-1/alcohol blend
    Autorzy:
    Gawron, B.
    Białecki, T.
    Dzięgielewski, W.
    Kaźmierczak, U.
    Powiązania:
    https://bibliotekanauki.pl/articles/244998.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    miniature jet engine
    alternative fuels
    exhausts emission
    Opis:
    This paper presents differences between fossil fuel (Jet A-1) and alcohol/Jet A-1 blend, during combustion process using laboratory test rig with miniature turbojet engine (MiniJETRig). The test rig has been created in Air Force Institute of Technology for research and development works aimed at alternative fuels for aviation. Fuel from different feedstock (non-fossil sources) is introduced into market due to ecological aspects, fuel price stability and energy security. Application of alcohol to propel aircraft has started form using a blend of aviation gasoline with ethanol in spark-ignited internal-combustion engines. Taking into account that large part of aviation fuels used by commercial aircraft is jet fuels, so in this area it has begun to look for possibilities to apply alcohol component. In 2016, international standard (ASTM) approved a synthetic blending component for aviation turbine fuels for use in civil aircraft and engines – alcohol-to-jet synthetic paraffinic kerosene (ATJ-SPK). According to standard, ATJ-SPK synthetic blending components shall be comprised hydro processed synthetic paraffinic kerosene wholly derived from isobutanol processed through dehydration, oligomerization, hydrogenation and fractionation. Two different fuel samples, a traditional fossil jet fuel (Jet A-1) and a blend of 10% butanol with Jet A-1 were tested. Laboratory tests of selected physicochemical properties and bench tests with the same profile of engine test were carry out for both fuel samples. The obtained results: engine parameters and exhaust gas emissions are compared and discussed.
    Źródło:
    Journal of KONES; 2016, 23, 1; 123-129
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Impact of work of turbine adaptive engines for the natural environment
    Autorzy:
    Ćwik, D.
    Kowalski, M.
    Steżycki, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/246614.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    noise of aircraft engines
    environmental impact
    jet engine turbine
    emission of toxic compounds
    aircraft engines
    turbine jet engine
    Opis:
    The article describes the problem of the operation of turbine jet, adaptive engine work on the natural environment. In particular, the analysis of noise generated by turbine jet engines has been made. It points out possible directions of noise decrease with particular emphasis upon structural changes within the engines, the task of which is to reduce the noise mission. The example of the modernization is based upon the “bypass” type of one-flow turbine jet engine. The essay contains theoretical basis of calculation of the noise emission level and the results, which graphically indicate a relative level of noise of this type of engine depending upon the amount of discharged air and the diameter of the discharge nozzle and the radius, upon the basis of which the noise level is determined. This work also includes a comparison of the relative noise level of this type of engine with regard to one-flow turbine engine equipped with the function of air discharge to the environment and with regard to two-flow turbine jet engine equipped with air stream flow mixing device. The use of low-emission combustion chambers in the "bypass" turbine engine was indicated. This allowed addressing the problem of emissions of toxic exhaust components by this type of aircraft engines. At the same time, the dependence of this emission related to the mass of fuel used on the engine's thrust range was indicated. The article was concluded with a short summary.
    Źródło:
    Journal of KONES; 2018, 25, 4; 509-516
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Researches of the dynamic characteristics of the turbine jet engine in flight based on its ground tests
    Autorzy:
    Golak, K.
    Lindstedt, P.
    Grądzki, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/247300.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    adjustment
    ground tests
    engine condition
    aircraft engine maintenance
    Opis:
    Turbine jet engines maintenance (adjustment) actions are performed during standard ground tests, but they are used during the flight. It turns out that the characteristics of the engine determined during the ground tests from the input value "w" introduced by the engine control lever DSS are significantly different from those obtained from disturbance “z" operating in the engine during the aircraft flight. It is noticed, that improvement of the engine control state made by mechanic during aircraft ground tests may cause the deterioration of the engine performance, which is felt by the pilot. The article presents a method that allows determining the basic characteristics of the engine in flight based only on the signals measured during testing ground. This method is based on measurement the major engine signals n – engine rpm, p4 – turbine discharge total pressure, p2 – low pressure compressor inlet, mp – fuel usage, then the designation of synthetic signals y=n/p4 (which describes the engine output), u=mp/p2 (describes engine input) and further their own and cross correlation function. Next, the power spectral density functions of these synthetic signals were calculated. Power spectral density functions is a basis to determine the spectral transfer function HW(jω) (during the ground tests) and HZ(jω) (in flight) which are the basis to determine the characteristics (step response) of the turbine jet engine in flight and during ground tests.
    Źródło:
    Journal of KONES; 2016, 23, 3; 151-156
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Jet fuels diversity
    Autorzy:
    Sarnecki, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/245076.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet fuel
    composition
    hydrocarbon
    jet engine
    fossil fuels
    surrogate fuels
    Opis:
    Term “jet fuel” is well known and recognized worldwide - it applies to aviation product used to power all turbine engines in aircrafts and helicopters. Its’ properties are clearly and strictly defined in international specifications. However, in the discussion concerning jet fuels, and in most research material, many people seem to forget that this fuel is a mixture of different hydrocarbons, is produced from different feedstock (crude oil from different sources available worldwide) and as a final product is obtained with different production processes. Thus, however jet fuel must meet the requirements defined in international standards, these fuels differ each other and as a result, differences can be observed in logistic chain and in combustion process. This paper points out some differences between jet fuels and its aim is to convict users, researchers and all people in aviation industry dealing with jet engines operation, that - when talking about jet fuel - many factors and details about final product must be considered, and this type of product should not be seen as single-type fuel, as most people see it now. The article has been prepared within the research project funded by the National Science Centre in Poland and granted with decision no. DEC-2011/01/D/ST8/06567.
    Źródło:
    Journal of KONES; 2014, 21, 4; 433-438
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    New Forms of Leading the Aviation Firms. International Perspectives of Future Trends in Global Aviation Industry
    Autorzy:
    Kalisz, David E.
    Czarnecki, Paweł S.
    Powiązania:
    https://bibliotekanauki.pl/articles/2158535.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Studiów Międzynarodowych i Edukacji Humanum
    Tematy:
    viation
    airline
    business model
    strategy
    competition
    jet engine
    Opis:
    Polish air transport is an important component of both the European and global transport services market. Enterprises and institutions responsible for its development should be conducive to shaping the most competitive position of entities of the air transport market. In Polish airports and branch infrastructural investments, balanced and sustainable development should be taken into account, determining the level of quality of services provided and access to the market. These aspects are highlighted in the strategy for the development of regional airports, whose task is also to stimulate the mobility of people and their transport activities. Air transport, although it is a relatively young form of transport, the history of which goes back over a hundred years back, is nowadays a very important element of the global economy. In the last decades the air passenger transport was treated as an elite one. It has now become very common and has contributed to the mobility of people in many regions of the world. More and more often, not only global companies or corporations are talked about, but also referring to the ease of moving, taking up work or studying in different parts of the world, away from the home country, people choose most often the air transportation.
    Źródło:
    Społeczeństwo i Edukacja. Międzynarodowe Studia Humanistyczne; 2018, 2(29); 27-36
    1898-0171
    Pojawia się w:
    Społeczeństwo i Edukacja. Międzynarodowe Studia Humanistyczne
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The comparative analysis of the selected construction types of axial compressor stage including the modal analysis
    Autorzy:
    Kozakiewicz, A.
    Grzejszczak, O.
    Lacki, T.
    Powiązania:
    https://bibliotekanauki.pl/articles/100091.pdf
    Data publikacji:
    2017
    Wydawca:
    Wrocławska Rada Federacji Stowarzyszeń Naukowo-Technicznych
    Tematy:
    modal analysis
    jet engine rotating parts
    BLISK
    optimisation
    Opis:
    The article concerns the issues of the scope of optimization of the gas turbine jet engine. These issues include limiting the weight and number of engine parts. One way to reduce the weight and number of components, including the compressor assembly, is to use the BLISK's replacement construction. The replacement construction should meet the strength requirement and the vibration spectrum as well. The paper presents a comparative analysis of the influence of rotational speed on the characters and the vibration frequency of the single rotor stage of the high pressure compressor. The analysis was carried out for two different design solutions of the blade-disk connection: the classical and integral. The comparative analysis focused on three important from the point of view of operation, the engine operating ranges: work on the ground (idle) and work during take-off and climb the aircraft.
    Źródło:
    Journal of Machine Engineering; 2017, 17, 4; 91-97
    1895-7595
    2391-8071
    Pojawia się w:
    Journal of Machine Engineering
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of measurement points sensitivity of vibration signals on the stand of jet engine
    Autorzy:
    Szymański, G. M.
    Misztal, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/133313.pdf
    Data publikacji:
    2017
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    vibration signal
    jet engine
    sygnał drganiowy
    silnik samolotowy
    Opis:
    The diagnostic testing of internal combustion engine can be made by using working processes and methods which take advantage of leftover processes. Working processes give information about general condition of internal combustion engine. Leftover processes give information about condition of particular subassemblies and kinematic couples; hence they are used as autonomous processes or as processes supporting other diagnostic methods. Methods based on analysis of vibrations and noise changes to determine technical condition of object are named as vibroacoustic diagnostics. In papers about vibroacoustic diagnostics of engine, problems connected with difficulty to select test point and to define diagnostic parameters containing essential information about engine’s condition, are most often omitted. Selection of engine’s working parameters and conditions of taking measurements or recording vibration signal are usually based on references, researcher’s experience or intuition. General assumptions about taking measurements of signal closest to its source are most often used. This paper presents a new approach to vibroacoustic diagnostics of jet engine. Selection of measurement points of vibration signals on the basis of tests stand results was suggested and perform a sensitivity analysis of measurement points on the engine support.
    Źródło:
    Combustion Engines; 2017, 56, 4; 279-282
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Advantages of compressor downstream air partial bleed and supplying it downstream of the turbine in a turbojet engine
    Autorzy:
    Ćwik, D.
    Kowalski, M.
    Stężycki, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/247092.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aviation engine operating parameters
    jet engine designs
    aviation engine air bleed
    Opis:
    The research article discusses the advantages of using compressor downstream air partial bleed and supplying it downstream of the turbine, which was applied in a prototype of a “bypass” turbojet engine. The objective of such a turbo engine structural solution was discussed along with its elements and principle of operation. Further part of the article determines the impact of such partial air bleed on the value of achieved basic operating parameters of the engine, i.e., unit thrust and unit power consumption. The presented attempt to compare these parameters with the parameters achieved for a turbojet, single flow engine is very important; in the first case without air bleed, and in the second, with air bleed to the environment. Further sections of the article compared these parameters relative to a turbojet, turbofan engine with a jet mixer. Such comparisons enabled to determine the actual benefits of using compressor downstream air partial bleed and supplying it downstream of the turbine, which may constitute an intermediate solution between single flow turbine engines and turbo fan engines. Wide possibilities for the application of such structural solutions were shown, which was summarised in the conclusions.
    Źródło:
    Journal of KONES; 2018, 25, 4; 501-508
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Numerical analysis of the intake vortex formation in the case of a double fuselage shielded inlet
    Autorzy:
    Kozakiewicz, A.
    Frant, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/281631.pdf
    Data publikacji:
    2014
    Wydawca:
    Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
    Tematy:
    turbine jet engine
    inlet intake vortex
    computational fluid Dynamics
    Opis:
    The paper raises a very important problem, concerning the work of turbine-jet engines, that is the intake vortex. A phenomenon which is relevant to all engines of this type. The article demonstrates literature data determining the influence of the airflow direction and zone on the possibility of vortex formation, taking into consideration the influence of basic geometrical data. The outcomes of calculations related to the formation of the inlet vortex for a given fuselage shielded inlet constructional system are shown. The studies are concerned with determination of the influence of angles and the gust speed value on forming of the vortex in this kind of intake.
    Źródło:
    Journal of Theoretical and Applied Mechanics; 2014, 52, 3; 757-766
    1429-2955
    Pojawia się w:
    Journal of Theoretical and Applied Mechanics
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Flow modeling in a jet engine
    Autorzy:
    Hlavńa, V.
    Rajčan, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/247566.pdf
    Data publikacji:
    2010
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    flow
    experimental approach
    numerical approach
    analytical approach
    Opis:
    It is possible to monitor effects related to flow in a jet aircraft engine by the three basic approaches - analytical, numerical and experimental Each approach has undergone changes and has been developed to the stage of its effective use. To efficiently manage the scientific and research work it is appropriate to use effective links among all three basic approaches. An experimental approach requires a test stand on which the characteristics of a usually geometrically reduced object or the actual object itself are verified. The principles of geometric and hydrodynamic similarities are applied. This approach is time and economically demanding and not all aerodynamic processes can be reliably simulated. Other disaavantages can be the occurrence of measurement errors, errors due to changes in the scale, influences of chemical reactions and influence of Reynolds number. Due to a very fast onset, development and challenges of IT, the numerical approach has become mostly used. It can provide sufficient information on an examined phenomenon in a particular object. It does not need any substantial simpliflcations, it is less financially demanding than the experimental approach, but it needs efficient processors with a huge memory capacity. Its disadvantage is a relatively large dependence of achieved results accuracy on the perfection of numerical models and models of turbulence in the areas with prevailing influence ofviscosity. The usage ofanalytical relations from mathematical andphysical analysis of the flow fleld is the fundamental of the analytical approach of observing the laws related to flowing. The paper deals with possibilities, procedures, advantages, and disadvantages of the mentioned approaches together with a presentation of some results from research and development activities carried out by the authors.
    Źródło:
    Journal of KONES; 2010, 17, 4; 191-197
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Influence of selected parameters on micro gas turbine compressor design
    Autorzy:
    Czarnecki, M.
    Olsen, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/243625.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    gas turbine
    design
    trend prediction
    centrifugal compressor
    Opis:
    The design a micro gas turbine engine is a process that requires analysis of a number of parameters. The initial stage requires consideration of more than 40 parameters [3]. The whole analysis can be made with analytical tools. However, these kinds of tools are limited to preliminary designs. After 1D-calculations and the establishment of the first CAD model, it is recommended to identify the sensitivity of the design. With a modern numerical environment such as ANSYS CFX, it is possible to predict a trend that gives the designer a 3D feedback about the initial design behaviour. For presented centrifugal compressor case, the selected parameters are vaneless diffuser space, design angle and number of stator blades. For qualitative evaluation – important results that influence design are mass flow rate, total pressure and isentropic efficiency. These results are important to turbojet engine performance and efficiency. All chosen parameters respond to given criteria. Validation and verification is still required due numerical errors that are included in CFD modelling. The advantage of 3D prediction is the possibility to eliminate gross errors before parts are sent into production.
    Źródło:
    Journal of KONES; 2017, 24, 3; 45-52
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    On the need to maintain homogenous temperature field within the working agent at the intake of a jet engine turbine
    Autorzy:
    Pawlak, W. I.
    Błachnio, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/245331.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    turbine jet engine
    simulation model
    working agent temperature field
    Opis:
    The paper presents results from numerical experiments with use of the computer model of the SO-3 engine designed for simulations. The model has been purposefully modified to take account of the assumed nonhomogeneity of the temperature field within the working agent at the turbine intake. It turned out that such nonhomogeneity substantially affects dynamic and static properties of the engine are considered as an object of control since it leads to a lag of the acceleration time and to increasing in fuel consumption. The summarized simulation results demonstrate that the foregoing properties of a jet engine are subject to considerable deterioration in pace with gradual increase of the assumed non-homogeneity of the temperature field, The simulations made it possible to find out that variations of the temperature field non-homogeneity within the working agent at the turbine intake lead to huge fluctuation of the turbine rpm for the idle run, which enables a new look to the role of the so-called idle run valve and importance of that component within the supply and control system of the SO-3 engine.
    Źródło:
    Journal of KONES; 2014, 21, 1; 205-213
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of the gust impact on inlet vortex formation of the fuselage-shielded inlet of an jet engine powered aircraft
    Autorzy:
    Kozakiewicz, A.
    Frant, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/279399.pdf
    Data publikacji:
    2013
    Wydawca:
    Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
    Tematy:
    turbine jet engine inlet
    intake vortex
    numerical fluid dynamics
    Opis:
    Selected problems of a complex structure, namely the fuselage-shielded inlet model of a turbine jet engine for numerical analysis purposes of the intake vortex formation phenomenon are presented in this paper. As a result of numerical analysis, an intake vortex has been developed. The analysis of the impact of changes in speed, angle and the direction of gust on vortex development has been conducted. Also, consequences of ingestion of foreign objects by the inlet and relevant statistics concerning damage to turbine engines have been presented.
    Źródło:
    Journal of Theoretical and Applied Mechanics; 2013, 51, 4; 993-1002
    1429-2955
    Pojawia się w:
    Journal of Theoretical and Applied Mechanics
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Detection damage in bearing system of jet engine using the vibroacoustic method
    Autorzy:
    Żokowski, M.
    Majewski, P.
    Spychała, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/970580.pdf
    Data publikacji:
    2017
    Wydawca:
    Politechnika Białostocka. Oficyna Wydawnicza Politechniki Białostockiej
    Tematy:
    jet engine
    damage of bearing
    vibroacoustic method
    envelope method
    Opis:
    The article discusses typical, operational systems for monitoring vibrations of jet engines, which constitute the propulsion of combat aircraft of the Armed Forces of the Republic of Poland. After that, the paper presents the stage of installing vibration measuring sensors in the direct area of one of the jet engine bearings, which is a support system for its rotor. The article discusses results of carried out analyses of data gathered during tests of the engine in the conditions a jet engine test bed. Results of detecting damages to the bearing, using sensors built in the direct area will be presented.
    Źródło:
    Acta Mechanica et Automatica; 2017, 11, 3; 237-242
    1898-4088
    2300-5319
    Pojawia się w:
    Acta Mechanica et Automatica
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Jet aircraft data acquisition systems
    Autorzy:
    Rojewski, A.
    Bartoszewicz, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/243996.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aircraft
    safety
    jet engine
    aviation
    samolot
    bezpieczeństwo
    silnik odrzutowy
    lotnictwo
    Opis:
    The article presents systems, which record parameters of flight in modern aircraft F-16, which was delivered to Polish Airforce in 2006. With the current level of technical development of the aviation industry, data acquisition systems are an important element of all aircrafts. These systems are responsible for the flight safety, allow reading and storing the most important flight parameters, and combined with digital control and safety systems allow to counteract dangerous situations, which especially can happen often in the case of military aircraft such as the F-16 due to their combat purpose. Systems records basics parameters of plane and engine, as specific fuel consumption or height of flight provides video and audio recording, and aerial combat assistance. These systems record even failures of a braking system during landing. Thanks to modern technology, and devices like those described in this article, F-16 is one of the best fighters in the world. The amount of data provided by analogue and digital sensors is so large that it requires the partitioning of parameters and use of several basic recorders of the entire system is the unit called DAU, or Data Acquisition Unit, which records the most important flight parameters, such as flight time, engine speed, or altitude.
    Źródło:
    Journal of KONES; 2018, 25, 1; 333-338
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Method of regulation condition assessment of turbine jet engine in flight basing on signals recorded during ground tests
    Autorzy:
    Golak, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/246520.pdf
    Data publikacji:
    2012
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    regulation
    computer simulation
    turbine jet engine
    parametric diagnostics
    ground tests
    Opis:
    During exploitation process operation quality differences may be observed between each particular machine and occurring in exploitation of one machine. These differences result from deviations of realized service process. Turbine jet engine regulation process was realized during ground tests. However, due to varying reactions of engines to external distortions, such as rocket launching, air swirl from another plane etc. as well as lack of possibility of simulation of in-flight conditions on ground (e.g. by partial choking of air intake), a situation may occur in which engine properly regulated on ground may not present sufficient efficiency in flight. Hence, the necessity to assess turbine jet engine regulation condition in flight basing on its ground tests. Research realized on computer models presenting engine operation both in flight and during ground tests indicated that real possibility of engine in flight regulation condition assessment based on its ground tests does exist. As was also noticed, with known input signal “w” and output signal “yW” recorded during engine ground tests as well as input “e” and output “u” signals from regulator during given test spectral powers and cross spectral powers of signals Swyw, Sww, See, Seu may be calculated and thus HW transfer function describing engine operation during ground test and GR transfer function describing regulator operation during given test and hence obtain transfer function HZ describing engine in flight. This grants possibility of regulation condition assessment of turbine jet engine in flight using signals recorded during ground tests.
    Źródło:
    Journal of KONES; 2012, 19, 3; 125-134
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of turbofan engine design modification to add inter-turbine combustor
    Autorzy:
    Jakubowski, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/244764.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    turbofan engine
    turbofan engine design
    airplane engine development
    inter turbine combustor turbofan
    Opis:
    An inter turbine combustion is one of modern direction of turbofan engine cycle modification. It is possible to reduce gas temperature in high-pressure turbine inlet section and reduce NOX emission by an additional combustor placed between high and low pressure turbines. The analysis of engine cycle modification and its performance are a scope of many scientific investigations, but it is not any work about engine dimension change due to cycle modification. By these way problems of two combustor engine components and dimensions, change with comparison to conventional turbofan engine is a goal of this work. The structure of a turbofan engine with inter turbine combustor is shown and results of evaluation temperature and pressure in specified engine cut sections are presented and discussed. Then the gas density is calculated and by mass continuity equation application, the specified cross section areas are determined. The results of two-combustor turbofan engine are compared with conventional high bypass turbofan engine. The comparison of engines parameters allow to predict how engine components should be modified in two-combustor turbofan when the base of modification is classic turbofan engine. The analyse contain determination of compressor and turbine stage numbers, prediction of areas of cross section and diameters in specified engine sections and overall engine axial dimensions. The results are used to formulate conclusion about the turbofan engine structure modification by additional combustor implementation between turbines.
    Źródło:
    Journal of KONES; 2015, 22, 3; 75-82
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Influence of Axial Compressor Model Simplification and Mesh Density on Surge Margin Evaluation
    Autorzy:
    Muchowski, Rafał
    Gubernat, Sławomir Maciej
    Powiązania:
    https://bibliotekanauki.pl/articles/2023311.pdf
    Data publikacji:
    2021
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    CFD
    axial compressor
    surge margin
    jet engine
    compressor map
    grid dependence
    Opis:
    The menace of surge occurrence in the compressors is taken very seriously and its avoidance became a fundamental for the design of any modern jet engines. Nowadays, a problem with appropriate evaluation of the compressor surge margin while considering different simplifications of three-dimensional CFD model is still present. For that purpose, this article presents a comparison between the measurement data and several variants of 3D CFD models characterized by a specific mesh density. To calculate all the results on which the comparisons and conclusions are based, an 8-stage axial compressor is taken into account. Flow conditions of the machine are computed for three part load speeds: The low, the mid and the high one respecting the variable guide vanes schedule fitted to the specific load. For each of speed variants a four mesh configurations were generated: coarse, medium, fine and extra-fine. All speed configurations were treated with two different turbulence models – Wilcox k-ω and Menter’s SST k-ω, giving ultimately 15 CFD models, calculated with the TRACE solver using an initialization based on a circumferentially averaged flow solution delivered by the Streamline Curvature Method. During the study an additional assessment of reference grid independence was performed and the mesh convergence has been achieved. A comparison between turbulence models and the measurement proves that SST turbulence model is not well distributed through the speeds in compare to the measurement data and the Wilcox turbulence model. Inconsistency of sensitivity in the mesh coarsening for different rotational speeds was found. Increasing the mesh roughness level has to be executed for each speed separately. Overall compressor map shows that shift of the Pressure Ratio and the Mass Flow decreases with lower rotational speed. Neglecting the system add-ons like labyrinth sealing volumes, bleed-ports and other leakages has a visible influence on deviations from the measurements. Because of intended future use in design and optimization the “Medium” grid with Wilcox k-ω turbulence model was chosen, being a good representation of the Rig characteristics with reduction of the computing time.
    Źródło:
    Advances in Science and Technology. Research Journal; 2021, 15, 3; 243-253
    2299-8624
    Pojawia się w:
    Advances in Science and Technology. Research Journal
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Selected problems of RD-33 engine reliability in operation
    Wybrane problemy niezawodności eksploatacji silników RD-33
    Autorzy:
    Trelka, M.
    Bartoszewicz, J.
    Urbaniak, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/134222.pdf
    Data publikacji:
    2016
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    jet engine
    powertrain
    aircraft malfunction
    silnik odrzutowy
    zespół napędowy
    uszkodzenia samolotu
    Opis:
    The paper presents an analysis of the most common damage incidents of the RD-33 turbine jet engine. Extended research on the assessment of powertrain reliability enabled a detailed identification of the causes of individual damage incidents along with possible threats. The presented statistical data related to the frequency of occurrence of individual damage incidents in recent years are particularly noteworthy. RD-33 is a newly designed engine, yet, in recent years it has gathered a very good opinion in the Polish Air Force, the effect of which are the efforts made by the military services and scientists aiming at the extending its proper and trouble free operation.
    W artykule zaprezentowano analizę głównych uszkodzeń związanych z eksploatacją turbinowego silnika odrzutowego RD-33. Długoletnie badania związane z oceną niezawodności zespołów napędowych umożliwiły szczegółową identyfikację przyczyn powstawania poszczególnych uszkodzeń, wraz z występującymi zagrożeniami. Na szczególną uwagę zasługują przedstawione dane statystyczne związane z częstością występowania poszczególnych rodzajów uszkodzeń w ostatnich latach. Silnik RD-33 nie należy do konstrukcji najnowocześniejszych, jednak w ciągu ostatnich lat zyskał w Siłach Zbrojnych RP bardzo dobrą opinię, czego wynikiem są prace podejmowane przez służby wojskowe i środowisko naukowe zmierzające do wydłużenia jego prawidłowej i bezproblemowej eksploatacji.
    Źródło:
    Combustion Engines; 2016, 55, 2; 33-40
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Ocena wpływu położenia punktu poboru spalin na wartość stężenia związków szkodliwych w strudze gazów wylotowych silnika odrzutowego
    The impact assessment of probe positioning for the exhaust gases concentration of the jet engine
    Autorzy:
    Markowski, J.
    Pielecha, J.
    Jasiński, R.
    Ślusarz, G.
    Wirkowski, P.
    Benedict, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/316559.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Naukowo-Wydawniczy "SPATIUM"
    Tematy:
    emisja spalin
    silnik odrzutowy
    sonda pomiarowa
    emission exhausts
    jet engine
    probe
    Opis:
    Emisja związków szkodliwych zawartych w spalinach zależy w od warunków eksploatacji silnika oraz jego stanu technicznego. W związku z tym działalność ustawodawcza ukierunkowana jest na wprowadzanie nowych procedur diagnostycznych i badawczych. Preferowana jest metoda z wykorzystaniem wielootworowych sond pomiarowych do wielopunktowego poboru spalin z całego przekroju strugi wypływających spalin. Taki pobór próbki spalin wydaje się obarczony błędem uśrednienia i rozcieńczenia pobranej próbki gazu już na samym początku drogi pomiarowej. Dlatego w artykule przedstawiono pomiary związane ze zmianą stężenia związków szkodliwych w spalinach w zależności od odległości od osi strugi. Podkreślono wady metody i przedstawiono propozycję pomiaru jednopunktowego.
    Emission of harmful compounds in the exhaust gases depends on the operating conditions of the engine and its technical condition. Therefore, the legislative activity is focused on the introduction of new diagnostic and research procedures. The preferred method is using probes with plurality of holes for multi-gas sampling from the entire cross-section of exhaust stream. This method appears to vitiated by an error caused by averaging dilution and sampling gas from the very beginning of the measurement path. The results of measurements contained in the article are related to changes in the concentration of harmful substances in exhaust gases depending on the distance from the axis of the jet. In the article the disadvantages of this the methods were highlighted and the single-point measurement method was proposed.
    Źródło:
    Autobusy : technika, eksploatacja, systemy transportowe; 2016, 17, 12; 1195-1198
    1509-5878
    2450-7725
    Pojawia się w:
    Autobusy : technika, eksploatacja, systemy transportowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Noise emission level versus the structure of the aircraft turbine engine
    Autorzy:
    Kowalski, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/241859.pdf
    Data publikacji:
    2012
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    noise of aircraft engines
    environmental impact of a jet engine turbine
    Opis:
    This article presents the problem of noise generated by turbine jet engines. It points out possible directions of noise decrease with particular emphasis upon structural changes within the engines, the task of which is to reduce the noise mission. The example of the modernization is based upon the "bypass" type of one-flow turbine jet engine. The essay contains theoretical basis of calculation of the noise emission level and the results, which graphically indicate a relative level of noise of this type of engine depending upon the amount of discharged air and the diameter of the discharge nozzle and the radius, upon the basis of which the noise level is determined. This work also includes a comparison of the relative noise level of this type of engine with regard to one-flow turbine engine equipped with the function of air discharge to the environment and with regard to two-flow turbine jet engine equipped with air stream flow mixing device. The essay ends with short conclusions. In order to struggle with the air noise special "Environmental Protection Programmes" are prepared. Civil airports and military airports prepare new procedures for taking off and approaching planes as well as optimize the approach and take off airport flight zone corridors. Unfortunately, in the case of so big surfaces, acoustic screens would not bring desired effects, also due to costs.
    Źródło:
    Journal of KONES; 2012, 19, 4; 325-332
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Modern methods of identification design conditions for single stage micro scale centrifugal compressor
    Autorzy:
    Czarnecki, M.
    Olsen, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/243293.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    gas turbine
    design
    off design
    trend prediction
    centrifugal compressor
    Opis:
    Micro scale gas turbine engines are low cost engines. They share their compressor impeller with automotive turbochargers. An identified design condition for the selected impeller is a critical stage of the design process. This process is had difficulties due the large number of manufacturers that provide OEM parts. It is common practice that one OEM part number provides the same impeller at different design revision. In general, parts are interchangeable but in detail, they differ slightly in terms of dimensions and performance. To avoid under predict or over predict inputs data, it is important to check the design parameters with as many methods as possible. In practice, the designer could rely on analytical methods, which are straightforward limited to the applied design. When shared its (compressor operation) it is recommended additional information be provided by computational fluid dynamics that produces a three-dimensional look into the predesign. That allows avoidance of future design failure and reduces both design time and prototype manufacturing costs.
    Źródło:
    Journal of KONES; 2017, 24, 2; 73-84
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Badania emisji związków szkodliwych spalin turbinowego silnika odrzutowego podczas przedstartowej próby samolotu SU-22
    Emission tests of turbine jet engine during prestart test of the SU-22
    Autorzy:
    Cwojdziński, L.
    Merkisz, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/316315.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Naukowo-Wydawniczy "SPATIUM"
    Tematy:
    silnik odrzutowy
    aparatura pomiarowa
    skażenie powietrza
    jet engine
    measuring apparatus
    air pollution
    Opis:
    W artykule przedstawiono wyniki badańemisji związków szkodliwych spalin silnika turbinowego samolotu Su-22, przeprowadzonych w warunkach przedstartowej próby silnika realizowanej na płycie lotniska. W artykule przedstawiono wyniki badań i ich analizę, pozwalającą na dokonanie oceny możliwości wykorzystania tego typu testów stacjonarnych do oceny emisji związków toksycznych spalin z turbinowych silników odrzutowych.
    The paper presents the results of exhaust gas emissions research for the Su-22 aircraft engine, conducted in the prestart engine test on the apron. The paper presents the measurements results and their analyses helping to assess if it is possible to use these kind of stationary tests in the toxic emission compounds evaluation from turbine jet engines.
    Źródło:
    Autobusy : technika, eksploatacja, systemy transportowe; 2013, 14, 3; 253-258
    1509-5878
    2450-7725
    Pojawia się w:
    Autobusy : technika, eksploatacja, systemy transportowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The assessment of the technical condition of SO-3 engine turbine blades using an impulse test
    Autorzy:
    Milewicz, Julia
    Mokrzan, Daniel
    Szymański, Grzegorz M.
    Powiązania:
    https://bibliotekanauki.pl/articles/2097507.pdf
    Data publikacji:
    2021
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    jet engine
    turbine
    modal analysis
    resonance
    silnik odrzutowy
    turbina
    analiza modalna
    rezonans
    Opis:
    The paper presents the effects of the application of an experimental impulse test as a method of diagnosis of the technical condition of an SO-3 engine turbine blade fitted in a TS-11 Iskra aircraft. The aim of the test was to investigate the frequency characteristics of the blades and discuss differences between the frequency spectrum of the investigated component before and after its damage. The acoustic response measurements were performed to the signal generated by an impact hammer on the fully functional and intentionally damaged blades. The recorded signals were converted from the domain of time to the domain of frequency using the Fast Fourier Transform (FFT). The results of the FFT were the Frequency Response Functions (FRF) of the sound of the blades, based on which the statistical analysis of the resonance frequencies was carried out. The influence of the mechanical damage of the blade on the shape and characteristics of the frequency spectrum was confirmed, which substantiated the effectiveness of the impulse test in the diagnostic assessment of jet engine components.
    Źródło:
    Combustion Engines; 2021, 60, 1; 24--29
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Exhaust emissions of jet engines powered by biofuel
    Autorzy:
    Merkisz, Jerzy
    Jasiński, Remigiusz
    Łęgowik, Anna
    Olejnik, Aleksander
    Powiązania:
    https://bibliotekanauki.pl/articles/2098181.pdf
    Data publikacji:
    2021
    Wydawca:
    Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
    Tematy:
    aviation
    exhaust emissions
    jet engine
    biofuel
    lotnictwo
    emisja spalin
    silnik odrzutowy
    biopaliwo
    Opis:
    Biofuel use is one of the basic strategies to reduce the negative impact of aviation on the environment. Over the past two decades, a number of biofuels produced from plants, lubricants and maintenance products have been developed and introduced. New fuels must have specific physicochemical parameters and meet stringent standards. his article presents a comparative analysis of the exhaust emissions measurement results from jet engines powered by traditional aviation kerosene and its blends with ATJ (Alcohol to Jet) biofuel. The concentrations of carbon dioxide, carbon monoxide and hydrocarbons were measured. Measurements were conducted in laboratory conditions for various engine load values. Based on the analysis, it was found that the use of biofuel increases the concentration of carbon monoxide and hydrocarbons in the exhaust gas relative to aviation kerosene. The use of biofuel did not result in an increase in fuel consumption and related carbon dioxide emissions. Based on the conducted research, it was found that biofuel use did not affect the ecological properties of the engine significantly. In addition, a correlation analysis of the measurement results from both engines was carried out.
    Źródło:
    Transport Problems; 2021, 16, 4; 199--206
    1896-0596
    2300-861X
    Pojawia się w:
    Transport Problems
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The emissivity of the turbine engine powered by biofuel
    Emisyjność turbinowego silnika zasilanego biopaliwem
    Autorzy:
    Pielecha, J.
    Jasiński, R.
    Markowski, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/195754.pdf
    Data publikacji:
    2017
    Wydawca:
    Politechnika Rzeszowska im. Ignacego Łukasiewicza. Oficyna Wydawnicza
    Tematy:
    biofuel
    jet engine
    emission
    air transport
    biopaliwo
    silnik odrzutowy
    emisja
    transport lotniczy
    Opis:
    Air transport is the youngest and most dynamically developing branch of transport. Growth in demand for air transport, both passenger and freight, is caused by the competitiveness of this branch primarily in terms of time and transport safety. An increase in the volume of air traffic is associated with increased emissions, which is particularly important in the case of aircraft operations in the areas of airports. The main reason for the development of aircraft engines is the reduction of fuel consumption and exhaust emissions. Emission standards for aircraft engines certification marginally treat the issue of particulate matter emissions, which is associated with deterioration of visibility appearing as smog and contributes to lung and heart diseases. One of the solutions for limiting the negative impact of the aircraft on the environment is the use of alternative fuels. Production of biofuels in accordance with the principles of sustainable development, is an attractive alternative, especially because of the lack of space constraints of their production allows the geographical diversification of supply. The article presents the measurements results of jet engine GTM-120 exhaust emissions. The test engine was powered with Jet A-1 fuel with 50-percent addition of bioester. During the test concentration of carbon monoxide, hydrocarbons and particulate matter was measured. On the basis of the measurements, the effect of the use of biofuel on emissions was presented.
    Transport lotniczy jest najmłodszą i najbardziej dynamicznie rozwijająca się gałęzią transportu. Wzrost zapotrzebowania na przewozy drogą lotniczą, zarówno pasażerskie i towarowe wynika głównie z krótkiego czasu transportu oraz bezpieczeństwa. Wzrost wolumenu transportowego związany jest ze wzrostem emisji związków szkodliwych spalin, co jest szczególnie istotne w kontekście emisji na terenie lotnisk oraz obszarach do nich przyległych. Głównym celem rozwoju konstrukcji silników lotniczych jest zmniejszenie zużycia paliwa i redukcja emisji związków toksycznych. Procedury certyfikacyjne dla silników odrzutowych marginalnie traktują zagadnienie cząstek stałych, które są powodem pogorszenia widzialności oraz chorób płuc i serca. Jednym z rozwiązań ograniczających wpływ transportu lotniczego na środowisko jest stosowanie paliw alternatywnych. W artykule przedstawiono wyniki pomiarów emisji związków szkodliwych silnia odrzutowego GTM-120. Badany silni zasilany był paliwem Jet A-1 oraz mieszanką nafty lotniczej z biopaliwem. Podczas badań zmierzono wartości stężenia tlenku węgla, węglowodorów oraz cząstek stałych. Na podstawie przeprowadzonych badań przedstawiono wpływ zastosowania biopaliwa na emisję związków szkodliwych.
    Źródło:
    Zeszyty Naukowe Politechniki Rzeszowskiej. Mechanika; 2017, z. 89 [295], 1; 85-98
    0209-2689
    2300-5211
    Pojawia się w:
    Zeszyty Naukowe Politechniki Rzeszowskiej. Mechanika
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Badanie emisji cząstek stałych z silników odrzutowych małych samolotów
    The study of particulate emissions from small aircraft equipped in jet engine
    Autorzy:
    Pielecha, J.
    Merkisz, J.
    Markowski, J.
    Jasiński, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/133105.pdf
    Data publikacji:
    2015
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    silnik odrzutowy
    cząstki stałe
    związki szkodliwe spalin
    jet engine
    particulate matters
    exhaust emission
    Opis:
    W artykule przedstawiono analizę rozkładu wymiarowego średnic cząstek stałych, emitowanych z turbinowego silnika lotniczego. Pomiary przeprowadzono w warunkach stacjonarnych symulując rzeczywiste warunki pracy silnika odrzutowego. Badania wykonano dla trzech początkowych faz pracy silnika: rozruchu, nagrzewania oraz pracy ustalonej. Otrzymane wyniki pozwoliły na wyznaczenie średnic cząstek stałych najczęściej występujących w danych warunkach, a jednocześnie skorelowano zmiany średnic cząstek stałych ze stężeniem gazowych związków szkodliwych spalin. W rezultacie otrzymano charakterystyki, na podstawie których stwierdzono, że rozkład wymiarowy średnic cząstek stałych w początkowej fazie pracy silnika charakteryzuje się dużą zmiennością. W pierwszym okresie pracy silnika dominują cząstki stałe o średnicach 20–30 nm oraz średnicach dużych (rzędu 100–140 nm), a w kolejnych okresach pracy ustabilizowanej dominują cząstki o średnicach z zakresu 30–40 nm.
    The article presents an analysis of the size distribution of particulate matters emitted from jet engine. Measurements were carried out in stationary conditions simulating real operating conditions of the jet engine. The study was performed for the three initial phases of engine operation: start-up, warm-up and steady-state operation. The obtained results allowed to determine the particulate matters size distribution of the most common particulates emitted under given conditions also the changes of characteristic diameters of particulate matters have been correlated with exhaust emission. As a result, the particulate matters size distributions were obtained on the basis of which it was found that diameters of particulates in the initial phase of engine operation are characterized by high variability. Th first period of engine operation is dominated by particles with diameters of 20–30 nm and bigger diameters (around 100–140 nm), and in next periods of engine operation particles are characterized by diameters in size range of 30–40 nm.
    Źródło:
    Combustion Engines; 2015, 54, 3; 376-382
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Badania wpływu dodatku tlenowego (CH3(OCH2CH2)3OCH3) do paliwa JET A-1 na emisję związków szkodliwych spalin silnika turbinowego GTM-120
    The investigation of the influence of the oxygen additive (CH3(OCH2CH2)3OCH3) to the JET A-1 fuel on the exhaust emissions from a GTM-120 turbine engine
    Autorzy:
    Merkisz, J.
    Markowski, J.
    Galant, M.
    Karpiński, D.
    Kubiak, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/133154.pdf
    Data publikacji:
    2013
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    silnik odrzutowy
    dodatki do paliw
    emisja spalin
    jet engine
    oxygen additive
    exhaust emissions
    Opis:
    Jednym z kierunków badań związanych z wpływem transportu na środowisko jest ograniczenie emisji szkodliwych składników spalin. W artykule przedstawiono wyniki przeprowadzonych badań i dokonano analizy możliwości wykorzystania paliwa JET A-1 z dodatkiem tlenowym (CH3(OCH2CH2)3OCH3) w silniku turbinowym GTM-120, bez modyfikacji silnika oraz zestawu elektroniki sterującej pracą silnika. Przeprowadzono ocenę wpływu różnych zawartości dodatku na emisję związków szkodliwych spalin, takich jak: tlenek węgla (CO), węglowodory (HC), tlenki azotu (NOx), dwutlenek węgla (CO2) oraz cząstki stałe (PM).
    One of the main trends in the research related to the influence of transport on the natural environment is the reduction of the exhaust emissions. The paper presents the results of investigations and analyses related to the potential for use of the JET A-1 with an oxygen additive (CH3(OCH2CH2)3OCH3) in a GTM-120 turbine engine without a modification of the engine and the engine control unit. An evaluation has been performed of the influence of different contents of the additive on the exhaust emission of such components as: carbon monoxide (CO), hydrocarbons (HC), nitric oxides (NOx), carbon dioxide (CO2) and PM (PM).
    Źródło:
    Combustion Engines; 2013, 52, 3; 769-774
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Korozja wysokotemperaturowa w transporcie
    High-temperature corrosion in transport
    Autorzy:
    Włodarkiewicz, A.
    Rokosz, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/311048.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Naukowo-Wydawniczy "SPATIUM"
    Tematy:
    silnik odrzutowy
    turbiny gazowe
    korozja wysokotemperaturowa
    jet engine
    gas turbine
    high-temperature corrosion
    Opis:
    Rozwój transportu samochodowego, kolejowego, morskiego jak i lotniczego jest jednym z ważniejszych wyzwań inżynierskich i logistycznych teraźniejszych czasów. Świat stając się "globalną wioską" wymusił rozwój głównie transportu lotniczego, ze względu na możliwość zwiększenia szybkości przewożenia ludzi oraz towarów na bardzo duże odległości, co w istotny sposób wpłynęło również na rozwój produkcji silników odrzutowych. Z tego względu korozja gazowa, która występuje w tych silnikach jest tematem nadal aktualnym zarówno dla przemysłu jak i nauki. W artykule omówiono między innymi zastosowanie silników odrzutowych w transporcie lądowym i powietrznym, materiały używane do ich produkcji, jak i mechanizmy korozji wysokotemperaturowej oraz metody jej zapobiegania.
    The development of car, rail, maritime and air transport are among the most important engineering and logistical challenges of modern times. The world's "global village" reality is accelerating the development of mainly air transport in the pursuit of developing high speed transfer of people and goods over very long distances, and this in turn has significantly contributed to the development of jet engines. Therefore, the gas corrosion that occurs in jet engines is a topic that is still relevant for both industry and science. In this paper, among other things, the use of jet engines in land and air transport, the materials used to produce them, as well as the mechanisms of high temperature corrosion and methods of preventing it, are discussed.
    Źródło:
    Autobusy : technika, eksploatacja, systemy transportowe; 2017, 18, 7-8; 442-445
    1509-5878
    2450-7725
    Pojawia się w:
    Autobusy : technika, eksploatacja, systemy transportowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Badania wpływu dodatku etanolu do paliwa Jet A-1 na emisję związków szkodliwych spalin silnika turbinowego GTM-120
    The investigations into the influence of ethanol additive to Jet A-1 fuel on the exhaust emissions from a GTM-120 turbine engine
    Autorzy:
    Merkisz, J.
    Markowski, J.
    Galant, M.
    Karpiński, D.
    Kubiak, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/132878.pdf
    Data publikacji:
    2013
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    silnik odrzutowy
    emisja spalin
    paliwa alternatywne
    etanol
    jet engine
    exhaust emissions
    alternative fuels
    ethanol
    Opis:
    W artykule przedstawiono badania silnika GTM-120 zasilanego Jet A-1 oraz paliwem Jet A-1 z dodatkiem etanolu (C2H5OH). Podczas badań mierzono zawartość głównych gazowych składników spalin CO, HC, NOx, CO2 oraz cząstek stałych. W badaniach wykorzystano analizator SEMTECH DS oraz spektrometr EEPS. Wyniki badań poddano analizie na podstawie której określono wpływ etanolu jako dodatku do paliwa Jet A-1 na emisję związków szkodliwych spalin.
    The paper presents the research on the GTM-120 engine fueled with Jet A-1 fuel and Jet A-1 fuel with the addition of ethanol (C2H5OH). During the tests the content of the main exhaust components in the exhaust gas was measured – CO, HC, NOx, CO2 and PM. In the tests the authors used a SEMTECH DS analyzer and an EEPS spectrometer. The results were subject to an analysis based on which the influence of ethanol as a fuel additive on the exhaust emissions was determined.
    Źródło:
    Combustion Engines; 2013, 52, 3; 775-780
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of Impact of Gust Angle and Velocity on the Position of Stagnation Point
    Autorzy:
    Frant, Michał
    Kozakiewicz, Adam
    Kachel, Stanisław
    Powiązania:
    https://bibliotekanauki.pl/articles/102313.pdf
    Data publikacji:
    2020
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    inlet vortex
    numerical fluid mechanics
    turbine jet engine
    wir wlotowy
    numeryczna mechanika płynów
    turbinowy silnik odrzutowy
    Opis:
    This paper presents the selected issues regarding the design of a complex object of a turbine jet engine inlet duct model for the purposes of numerical analysis related to the phenomenon of inlet vortex formation. The authors described the process of discretisation in the matter in question and presented certain guidelines for preparing and conducting discretisation of the computational area. The authors presented an exemplary test findings analysis to verify the accuracy of the object’s shape, computation grid as well as the selection of the boundary conditions and solution algorithm. The main part of the paper regards the analysis of changes in the location of the vortex (point of stagnation) based on an examination of the impact related to the changes in the velocity and inlet and gust angles. The authors sought to determine the areas and regularity of points of stagnation.
    Źródło:
    Advances in Science and Technology. Research Journal; 2020, 14, 4; 49-57
    2299-8624
    Pojawia się w:
    Advances in Science and Technology. Research Journal
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Parametry określające wejście lotniczego silnika turbinowego w niestateczną pracę sprężarki
    Parameters defining entry of the turbine engine into the unstable work of the compressor
    Autorzy:
    Kozakiewicz, A.
    Kowalski, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/213610.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    sprężarka osiowa
    pompaż
    lotnicze silniki turbinowe
    portret fazowy
    axial compressor
    surge
    turbine jet engine
    phase portrait
    Opis:
    W artykule przedstawiono przyczyny generowania nierównomiernego pola parametrów na wejściu do sprężarki lotniczego silnika turbinowego i ich wpływ na kinematykę strumienia powietrza przy obniżającej się wytrzymałości zmęczeniowej łopatki sprężarkowej. Dokonano analizy przebiegu zmian momentu obrotowego wirnika jako funkcji czasu. Przedstawiono przebiegi podstawowych parametrów pracy silnika turbinowego podczas wchodzenia w zakres niestatecznej pracy. Określono istotną rolę w tej ocenie zmian pierwszej pochodnej momentu obrotowego w relacji do zmian przyspieszeń wirnika, która może być istotnym sygnałem o możliwości wystąpienia pompażu w sprężarce. Parametr ten może być sygnałem dla układu sterowania do eliminowania tego szkodliwego zjawiska. Przedstawiono także dynamikę silnika wspartą badaniem podczas pompażu poprzez opracowanie portretów fazowych podstawowych parametrów jego pracy. Artykuł zawiera analizę dynamiki zmian temperatury spalin.
    This paper presents reasons for generating non uniform area of parameters on the entry to the compressor of the turbine engine and their influence on the air stream kinematics at the decreasing fatigue strength of the compressor blade. Analysis of the course of the torque rotor changes as the function of time was presented. Courses of basic parameters of the turbine engine work during the ingress into the range of unstable work were presented. The crucial role in this estimation of changes of the first differential of the torque in relation to changes in acceleration of the rotor which can be a significant signal of the possibility of surge occurrence in the compressor were defined. This parameter can be a signal for the control system to eliminate this bad phenomenon. The dynamics of the engine supported with the research during surge through the study of parameters'phase portraits of its work were also presented. The article contains analysis of the dynamics of changes in temperature of combustion gas.
    Źródło:
    Prace Instytutu Lotnictwa; 2016, 3 (244); 373-384
    0509-6669
    2300-5408
    Pojawia się w:
    Prace Instytutu Lotnictwa
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Estimation of fuel consumption in a jet engine based on vibration signal parameters
    Autorzy:
    Szymański, Grzegorz M.
    Cywka, Bartłomiej
    Mokrzan, Daniel
    Prokopowicz, Wojciech
    Powiązania:
    https://bibliotekanauki.pl/articles/24202474.pdf
    Data publikacji:
    2023
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    vibroacoustics
    jet engine
    fuel consumption
    estimation
    statistical analysis
    wibroakustyka
    silnik odrzutowy
    zużycie paliwa
    szacowanie
    analiza statystyczna
    Opis:
    This paper proposes the use of vibroacoustic signal parameters to estimate the fuel consumption of a miniature GTM-400 engine. The method for testing engine vibrations is presented, followed by an analysis of the results obtained. Two vibration point measures were selected to build a fuel consumption model. The models obtained were verified, after which those that best describe the real fuel consumption of the engine were selected. The paper proves that the vibration signal, in addition to its applications in jet engine diagnostics, can be used to determine engine performance, which can contribute to reducing the complexity of construction and increasing the economics of engine operation.
    Źródło:
    Combustion Engines; 2023, 62, 3; 13--20
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Numerical investigation on the effects of fueling the Turbulent Jet Ignition gas engine with methane and hydrogen
    Autorzy:
    Pielecha, Ireneusz
    Szwajca, Filip
    Skobiej, Kinga
    Powiązania:
    https://bibliotekanauki.pl/articles/32103224.pdf
    Data publikacji:
    2023-11-30
    Wydawca:
    Sieć Badawcza Łukasiewicz - Poznański Instytut Technologiczny
    Tematy:
    hydrogen engine
    engine simulation
    hydrogen combustion
    methane combustion
    combustion indicator
    turbulent jet ignition engine
    Opis:
    The modern solution of two-stage combustion, namely the Turbulent Jet Ignition (TJI), enables the combustion of ultra-lean mixtures. Thanks to this solution, it became possible to reduce fuel consumption and, at the same time, to increase the combustion process indicators (including the overall combustion system efficiency). The article presents the results of numerical tests of a heavy-duty engine equipped with the TJI system running on gas fuels. The AVL BOOST software was used to analyze the effects of different fuel injection rates into the pre-chamber and various ignition timing angles, while maintaining a constant global excess air ratio. Increasing the proportion of hydrogen in the prechamber resulted in its reduction in the main chamber (the fuel dose was kept constant with different excess air coefficients in each of the chambers). The maximum combustion pressure values in both chambers were investigated. Changes in the amount of heat released and its release rate were determined. As a result of the simulations, different ignition and combustion conditions were presented for the tested fuels. Based on this, maps of fuel dose to prechamber vs. ignition advance angle were drawn up, showing selected thermodynamic indicators of the combustion process.
    Źródło:
    Rail Vehicles/Pojazdy Szynowe; 2023, 1-2; 46-57
    0138-0370
    2719-9630
    Pojawia się w:
    Rail Vehicles/Pojazdy Szynowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Premises of Parametrical Assessment of Turbojet Engine in Flight Regulation Condition During Ground Test
    Autorzy:
    Lindstedt, P.
    Golak, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/387321.pdf
    Data publikacji:
    2012
    Wydawca:
    Politechnika Białostocka. Oficyna Wydawnicza Politechniki Białostockiej
    Tematy:
    regulacja
    symulacja komputerowa
    silnik odrzutowy
    diagnostyka
    test
    regulation
    computer simulation
    turbine jet engine
    parametric diagnostics
    ground tests
    Opis:
    The article presents the theoretical bases of method, engine technical condition is described by one (in other methods four are used) comprehensive model (binding engine input signals p2 and mp and engine output - n and p4 signals) with unique feature, that engine operation quality during ground tests will provide neccessary data on its performance in flight. The changes occurring in turbojet engine during its exploitation will be measure by comparision of standard model with parameters obtained from experiment (ground test).
    Źródło:
    Acta Mechanica et Automatica; 2012, 6, 1; 44-48
    1898-4088
    2300-5319
    Pojawia się w:
    Acta Mechanica et Automatica
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Usage of wing in ground effect to maintain lift force with reduced fuel consumption of aircraft
    Autorzy:
    Rojewski, A.
    Bartoszewicz, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/133656.pdf
    Data publikacji:
    2017
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    ekranoplan
    numerical analysis
    fuel consumption
    jet engine
    energy consumption
    analiza numeryczna
    zużycie paliwa
    silnik odrzutowy
    zużycie energii
    Opis:
    The main purpose of this article was to point out causes of reduced fuel consumption in aircraft jet engine when aircraft is in ground effect influence. Wing in ground effect occurs in the direct proximity of ground. The paper presents wing in ground effect description, with the numerical analysis of NACA M8 airfoil in three different conditions of flight. Numerical analysis was conduct in Ansys Fluent 17.2 software. The paper shows results of simulations which describes wing in ground effect influence on NACA M8 airfoil with two cases of jet engine exhaust gasses usage, first with exhaust gasses stream turns on upper airfoil surface, and second with exhaust gasses stream turns under lower airfoil surface. Results allow to define characteristics of NACA M8 airfoil in the influence of wing in ground effect which are lift coefficient, drag coefficient, drop of fuel consumption usage by the jet engine when lift force remains still in the wing in ground effect. The paper shows that in the wing in ground effect aircraft energy usage for flight in ground effect is smaller than for free air flight.
    Źródło:
    Combustion Engines; 2017, 56, 2; 158-161
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The effect of adding 2-ethylhexanol to jet fuel on the performance and combustion characteristics of a miniature turbojet engine
    Autorzy:
    Gawron, B.
    Białecki, T.
    Król, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/247180.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    alternative fuels
    alcohol to jet
    combustion process
    miniature jet engine
    exhaust emission
    paliwa alternatywne
    proces spalania
    miniaturowy silnik odrzutowy
    emisja spalin
    Opis:
    There are currently many studies undergoing in the field of using alternative fuels for supplying different types of propulsion units. The ASTM standard in the aerospace industry, allows using five different technologies of manufacturing synthetic components apart from standard oil-based fuel for the propulsion of turbine engines (as a blend up to 50% with conventional fuel). One of these is a technology associated with the process of converting alcohols (isobutanol) to jet fuel – Alcohol to Jet (ATJ). In the research performance, emission parameters were measured on laboratory test rig with miniature turbojet engine (MiniJETRig). The test rig has been created in Air Force Institute of Technology for research and development works aimed at alternative fuels for aviation. The miniature engine was fuelled with conventional jet fuel – Jet A-1 and blend of Jet A-1 with 2-ethylhexanol. The results for this blend were compared with the results obtained for neat Jet A-1 fuel in terms of different engine operating modes, according to specified methodology. The conducted tests did not show significant differences in engine operating parameters (thrust, fuel consumption and thrust specific fuel consumption) and the values of CO, CO2 and NOx emission indices between the tested fuels. The engine tests took place in similar ambient conditions. Laboratory tests of selected physicochemical properties were also carried out for both fuel samples.
    Źródło:
    Journal of KONES; 2018, 25, 1; 101-109
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Experimental determination of compressor map of the DGEN 380 engine compressor using the WESTT CS/BV turbine engine simulator
    Autorzy:
    Pazura, Karolina
    Orkisz, Marek
    Powiązania:
    https://bibliotekanauki.pl/articles/2097512.pdf
    Data publikacji:
    2021
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    compressor map
    engine bench
    turbofan jet engine
    turbine engine
    mass flow rate
    mapa kompresora
    ława silnika
    silnik turbowentylatorowy
    silnik turbinowy
    masowy wskaźnik szybkości płynięcia
    Opis:
    Currently aviation focuses mainlly on increasing the economy and ecology of engines. Production of NOx, CO2 and SO2 adversaly impacts the environment. Parallel goal to minimize SFC to achieve both lower: emission and mission costs. The optimization of components is thus very important. One of the ways of optimizing cycle is doing that based on compressor maps. However it is very expensive to plot one since experimental work needs to be done. The aim of this article is to present a methodology of creating compressor map based on ENGINE ANALOGY. There was used the virtual bench WESTT CS/BV for tests to receive pressure ratio and mass flow of DGEN 380 for three different values of flight speed and altitude, while the rotational speed was changed. The construction similarity of CFM 56-5B and APS 3200 gives the opportunity to plotted compressor maps using the engine analogy without the need for an experiment or using the virtual bench.
    Źródło:
    Combustion Engines; 2021, 60, 2; 26--31
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Emission of selected exhaust compounds in jet engines of a jet aircraft in cruise phase
    Autorzy:
    Pawlak, M.
    Majka, A.
    Kuźniar, M.
    Pawluczy, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/134256.pdf
    Data publikacji:
    2018
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    jet engine
    emission
    fuel consumption
    cruise phase
    ATM
    SESAR
    silnik odrzutowy
    emisja
    zużycie paliwa
    faza rejsu
    zarządzanie ruchem lotniczym
    Opis:
    Nowadays, air transport is in an intense development phase. In order to optimize air communication and make it even more economical and environmentally friendly, attempts are made to undertake such activities as, e.g., SESAR project, which aims to develop and implement a modern ATM system. One of the parts of this project is the research on minimizing fuel consumption and emissions of pollutants in the engine exhausts. In the paper there is therefore presented the methodology for determining emission of those pollutants for the longest stage of the flight - the cruise phase. First, the value of the thrust required for the flight of an exemplary aircraft was deter-mined, and then the values of the engines trust and specific fuel consumption were computed. Additionally, it was necessary to determine the Emission Indexes (EI) of CO, NOx, HC and CO2 for the cruise phase, based on known such indexes for the LTO. Total emissions of these pollutants for the mission adopted to conduct research - a 1000 km long cruise - were determined. These emissions were computed for the exemplary aircraft per one kilometre, as well as per one hour of flight for various cruising altitudes and flight speeds.
    Źródło:
    Combustion Engines; 2018, 57, 2; 67-72
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Estymacja punktu pracy sprężarki i jego parametrów w oparciu o charakterystyki sprężarek
    Estimating the compressors works point and its parameters based on performance of compressors
    Autorzy:
    Kozakiewicz, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/212550.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    sprężarka osiowa
    opływ palisady sprężarki
    pompaż
    turbinowe silniki odrzutowe
    axial compressor
    flow around grid of blades
    surge
    turbine jet engine
    Opis:
    W artykule przedstawiono problematykę związaną z estymacją punktu pracy sprężarki w oparciu ojej charakterystykę. Analizowano problematykę związaną z pracą poszczególnych stopni zespołu ze względu zmiany kąta natarcia strumienia w wyniku zmian prędkości obrotowych. Przedstawiono wyniki analizy numerycznej opływu stopnia sprężarki. Zanalizowano zmianę położenia linii pracy silnika w wyniku wyboru kąta natarcia na zakresie obliczeniowym. Zaprezentowano problematykę ze zmianą warunków pracy poszczególnych stopni sprężarki.
    This paper presents problems concerning the estimation of the point works of the compressor and its parameters based on its characteristics. Problems connected with the work of individual compressor stages regarding the change of the angle of attack stream as a result of changes in rotating velocities were analysed Results of the numerical analysis of the stage compressor's round flow were demonstrated. The- dislocation of the work line of the engine as a result of the choice of the angle of attack on the computational range were presented. Problems with modifying work conditions for individual compressor stages were presented.
    Źródło:
    Prace Instytutu Lotnictwa; 2016, 3 (244); 363-372
    0509-6669
    2300-5408
    Pojawia się w:
    Prace Instytutu Lotnictwa
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analiza porównawcza osiągów turbinowych silników odrzutowych samolotów bojowych obecnie użytkowanych w RP
    Comparative analysis of turbojet performance of combat aircraft used in Polish Air Force
    Autorzy:
    Kozakiewicz, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/210410.pdf
    Data publikacji:
    2009
    Wydawca:
    Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
    Tematy:
    turbinowe silniki odrzutowe
    efektywność dopalacza
    charakterystyka obrotowa silnika
    jet turbine engine
    effectiveness afterburner
    rotated characteristic engine
    Opis:
    Artykuł przedstawia analizę osiągów zespołów napędowych samolotów wielozadaniowych, obejmuje ona między innymi współczynniki strat samolotów jedno i dwusilnikowych. Dokonano oceny silników eksploatowanych w Siłach Powietrznych RP na samolotach F-16C, MiG-29 i Su-22. Wykonano obliczenia charakterystyki obrotowej silnika RD-33 i uzyskano charakterystyki ciągu silnika, jednostkowego zużycia paliwa, temperatury przed turbiną i stopnia podziału masowego natężenia w funkcji prędkości obrotowej wirnika wysokiego ciśnienia. Przedstawiono również obliczoną charakterystykę prędkościowo-wysokościową, która jest istotna z punktu możliwości wykonywania zadań przez każdy samolot - w tym szczególnie samoloty wielozadaniowe.
    This paper presents the analysis of performance of combat aircraft engines, including losses coefficients for single and double engines. Assessment of the engines used in the aircraft F-16C, MiG-29, and Su-22 engines in Polish Air Force has been made. Some rotated characteristic of RD-33 engine and characteristics of engine trust, specific fuel consumption, temperature before a turbine and a bypass ratio were calculated. Also the calculated speed-altitude characteristic, very important for each plane tasks and especially combat aircraft tasks, was presented.
    Źródło:
    Biuletyn Wojskowej Akademii Technicznej; 2009, 58, 2; 65-83
    1234-5865
    Pojawia się w:
    Biuletyn Wojskowej Akademii Technicznej
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Technologia zawieszeń magnetycznych w aspekcie zastosowania w elektrycznych silnikach odrzutowych
    Magnetic Suspension Technology for Electric Jet Engines
    Autorzy:
    Falkowski, Krzysztof
    Henzel, Maciej
    Kurnyta-Mazurek, Paulina
    Janczewski, Mariusz
    Ważny, Mariusz
    Powiązania:
    https://bibliotekanauki.pl/articles/2097745.pdf
    Data publikacji:
    2021
    Wydawca:
    Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
    Tematy:
    inżynieria mechaniczna
    silnik odrzutowy
    łożyska magnetyczne
    bezłożyskowe silniki elektryczne
    ogniwa paliwowe
    mechanical engineering
    jet engine
    magnetic bearing
    bearingless motors
    fuel cell
    Opis:
    Ograniczenie emisyjności szkodliwych związków, takich jak CO 2 i NOx, zostało uznane za priorytetowy cel w Unii Europejskiej. W lotnictwie, które jest jedną z branży o wysokim wskaźniku wytwarzania zanieczyszczeń, ograniczenie emisji zanieczyszczeń można uzyskać przez zastosowanie elektrycznych silników odrzutowych. Silniki takie konstrukcyjnie znacznie różnią się od silników napędzanych naftą lotniczą. Związane jest to przede wszystkim z wykorzystaniem energii elektrycznej jako źródła zasilania. W artykule przedstawiono koncepcję elektrycznego silnika odrzutowego, w którym wirnik łożyskowany jest magnetycznie. Zaprezentowano opracowane w Zakładzie Awioniki Instytutu Techniki Lotniczej WAT demonstratory technologii aktywnych i pasywnych łożysk magnetycznych, jak i bezłożyskowych silników elektrycznych, a także technologię zasilania hybrydowego z wykorzystaniem ogniw paliwowych.
    Reducing the emission of harmful compounds such as carbon dioxide and nitrogen oxides has been identified as a priority target in the European Union. Aviation is one of the main sources of pollution. The reduction of pollutant emissions can be achieved by the use of the electric jet engine. This type of a jet engine differs significantly from a kerosene-powered engine. The article presents the concept of an electric jet engine with the rotor that is magnetically suspended. Demonstrators of active and passive magnetic bearing technologies and bearingless electric motors, developed at the Avionics Department, are presented in the paper.
    Źródło:
    Biuletyn Wojskowej Akademii Technicznej; 2021, 70, 3; 49--70
    1234-5865
    Pojawia się w:
    Biuletyn Wojskowej Akademii Technicznej
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of wind impact on emission of selected exhaust compounds in jet engines of a business jet aircraft in cruise phase
    Autorzy:
    Pawlak, M.
    Majka, A.
    Kuźniar, M.
    Pawluczy, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/134098.pdf
    Data publikacji:
    2018
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    jet engine
    emission
    exhausts
    fuel consumption
    cruise phase
    Air Traffic Management
    ATM
    SESAR
    silnik odrzutowy
    emisja
    spaliny
    zużycie paliwa
    faza rejsu
    zarządzanie ruchem lotniczym
    Opis:
    Among the most important problems currently faced by air transport, we can distinguish the adverse impact of aircrafts on the natural environment, as well as the rising costs of transport. One of the possibilities to improve this situation is better adjustment of aircraft characteristics to the performed transport tasks, taking into account all the requirements and limitations that exist in air traffic and the adverse impact of air transport on the natural environment. It is reflected in the research tasks conducted under the SESAR program. The aspiration to minimize the adverse impact of aircrafts on the environment is executed, among others, through determining such trajectories that are characterized by minimal fuel consumption or minimal emission of harmful substances in the engines exhausts. These goals are corresponding with the research conducted and described in the paper. The main aim of the work was to analyse the impact of wind speed and direction on the emission of harmful substances of a jet aircraft performing a flight on a given route. For research purposes, the route between two Polish cities Gdansk and Rzeszow was considered. The distance between the two airports was divided into sections for which wind direction and strength were determined (read from the windy.com website). Next, the aircraft performance was determined and the fuel consumption and the amount of harmful compounds (CO2, NOx, CO and HC), emitted in the engines exhausts were determined for the route from Gdansk to Rzeszow (under favourable wind conditions) and on the return route - from Rzeszow to Gdansk (under unfavourable wind conditions). For comparative purposes, emission of these substances for windless conditions was also determined. The results are presented in tables and depicted in the graph, as well as discussed in the conclusions of the paper.
    Źródło:
    Combustion Engines; 2018, 57, 2; 55-60
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The influence of jet engine noise on hearing of technical staff
    Wpływ hałasu silników odrzutowych na słuch personelu technicznego
    Autorzy:
    Konopka, Wiesław
    Pawlaczyk-Łuszczyńska, Małgorzata
    Śliwińska-Kowalska, Mariola
    Powiązania:
    https://bibliotekanauki.pl/articles/2166206.pdf
    Data publikacji:
    2014-12-19
    Wydawca:
    Instytut Medycyny Pracy im. prof. dra Jerzego Nofera w Łodzi
    Tematy:
    hałas silników odrzutowych
    uszkodzenie słuchu
    audiometria tonalna
    emisja otoakustyczna produktów zniekształceń nieliniowych
    DPOAE
    jet engine noise
    hearing impairment
    pure tone audiometry
    distortion product otoacoustic emission
    Opis:
    Background: Due to high sound pressure levels (SPLs), noise produced by jet planes may be harmful to hearing of people working in their proximity. The aim of this study was to assess the effects of exposure to jet engine noise on technical staff hearing. Material and Methods: The study comprised 60 men, aged 24–50 years, employed in army as technical staff and exposed to jet engine noise for 6–20 years. The control group were 50 non-noise exposed males, aged 25–51 years. Exposure to noise emitted by jet engines was evaluated. Pure-tone audiometry (PTA) and distortion product otoacoustic emissions (DPOAE) were recorded in both groups. Results: Jet engines emitted broadband noise with spectrum dominated by components in the frequency range 315–6300 Hz (1/3-octave bands). Maximum A-weighted SPL during tests reached values of approx. 120–130 dB. Consequently, engine-servicing personnel (even in the case of a single engine test) was exposed to noise (at A-weighted daily noise exposure level above 95 dB) exceeding permissible levels. Averaged audiometric hearing threshold levels of technical staff were higher (≤ 17 dB HL, p < 0.001) than in the control group. Similarly, the DPOAE amplitude was lower (≤ 17 dB SPL, p < 0.01) in the noise-exposed subjects compared to the non-exposed ones. Significant reduction of DPOAE levels was mainly noted for high frequencies (3–6 kHz). Conclusions: Despite the usage of hearing protection devices, both PTA and DPOAE consistently showed poorer hearing in engine-servicing personnel vs. control group. Med Pr 2014;65(5):583–592
    Wstęp: Hałas emitowany przez silniki odrzutowe ze względu na wysoki poziom dźwięku może być szkodliwy dla słuchu osób pracujących w ich sąsiedztwie. Celem pracy była ocena wpływu ekspozycji na hałas na stan słuchu techników obsługujących silniki odrzutowe. Materiał i metody: Badaniami objęto 60 mężczyzn w wieku 24–50 lat, zatrudnionych w wojsku i narażonych na hałas silników odrzutowych przez okres 6–20 lat. Grupę porównawczą stanowiło 50 mężczyzn w wieku 25–51 lat nienarażonych zawodowo na hałas. Oceniono ekspozycję na hałas emitowany przez silniki odrzutowe. Diagnostykę słuchu oparto na badaniu audiometrią tonalną i rejestracji emisji otoakustycznych produktów zniekształceń nieliniowych (distortion product otoacoustic emissions – DPOAE). Wyniki: Silniki odrzutowe emitowały hałas szerokopasmowy, w którym dominowały składowe z przedziału częstotliwości 315–6300 Hz (pasma 1/3-oktawowe). Maksymalny poziom dźwięku A w czasie testów osiągał 120–130 dB. W konsekwencji, nawet w przypadku pojedynczego testu, personel obsługujący silniki był narażony na hałas (dzienny poziom ekspozycji (L EX, 8h) > 95 dB) przekraczający wartości najwyższych dopuszczalnych natężeń hałasu w środowisku pracy. Progi słuchu w grupie techników obsługujących silniki odrzutowe były wyższe (≤ 17 dB HL, p < 0.001) niż w grupie porównawczej. Amplituda emisji otoakustycznych DPOAE była również niższa (≤ 17 dB SPL, p < 0,01) u osób narażonych na hałas w porównaniu z nienarażonymi. Jej istotne statystycznie obniżenie stwierdzono głównie dla wysokich częstotliwości (3–6 kHz). Wnioski: Mimo stosowania ochronników słuchu zarówno wyniki audiometrii tonalnej, jak i DPOAE wskazywały na gorszy słuch u techników obsługujących silniki odrzutowe niż u osób z grupy porównawczej. Med. Pr. 2014;65(5):583–592
    Źródło:
    Medycyna Pracy; 2014, 65, 5; 583-592
    0465-5893
    2353-1339
    Pojawia się w:
    Medycyna Pracy
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Zastosowanie krótkoczasowej analizy częstotliwościowej do wyznaczenia częstotliwości wymuszeń odrzutowego silnika lotniczego na stanowisku badawczym
    Application of short time-frequency analysis to determine the extortion frequency of a jet aircraft engine on a test bench
    Autorzy:
    Szymański, G. M.
    Misztal, A.
    Misztal, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/310433.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Naukowo-Wydawniczy "SPATIUM"
    Tematy:
    JTFA
    Joint Time Frequency Analysis
    analiza częstotliwościowa drgań
    analiza czasowo-częstotliwościowa
    analiza drgań silnika odrzutowego
    silnik odrzutowy
    Joint Time-Frequency Analysis
    frequency analysis of vibrations
    jet engine
    Opis:
    Diagnostyka silników spalinowych w tym odrzutowych bazuje na metodach wykorzystujących procesy robocze oraz procesy resztkowe tj. drgania, hałas, procesy termiczne, elektryczne i inne. Na podstawie wyników badań procesów roboczych można wnioskować o ogólnym stanie technicznym silnika, natomiast procesy resztkowe niosą informacje o stanie poszczególnych podzespołów i par kinematycznych. Dlatego procesy resztkowe wykorzystuje się, jako autonomiczne lub wspomagające inne metody diagnostyczne. Wszystkie metody oparte na analizie zmian drgań i hałasu dla określenia stanu technicznego obiektu noszą nazwę diagnostyki wibroakustycznej. W pracach dotyczących diagnostyki wibroakustycznej silników, najczęściej pomija się zagadnienia związane z problemem wyboru pasma pomiarowego oraz określenia parametrów diagnostycznych zawierających istotne informacje o stanie silnika. W artykule przedstawiono metodę separacji składowych kinematycznych sygnału drgań z wykorzystaniem technik Joint Time Frequency Analysis (JTFA).
    The diagnostic testing of internal combustion engine can be made by using working processes and methods which take advantage of leftover processes (vibration, noise, thermic processes, electric and other). Working processes give information about general condition of internal combustion engine. Leftover processes give information about condition of particular subassemblies and kinematic couples; hence they are used as autonomous processes or as processes supporting other diagnostic methods. Methods based on analysis of vibrations and noise changes to determine technical condition of object are named as vibroacoustic diagnostics. In papers about vibroacoustic diagnostics of engine, problems connected with difficulty to select frequency band and to define diagnostic parameters containing essential information about engine’s condition, are most often omitted. This article describes the method of separation of kinematic components of vibration signal using the technique of Joint Time Frequency Analysis (Jtfa).
    Źródło:
    Autobusy : technika, eksploatacja, systemy transportowe; 2017, 18, 12; 1328-1332, CD
    1509-5878
    2450-7725
    Pojawia się w:
    Autobusy : technika, eksploatacja, systemy transportowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Turbinowe silniki odrzutowe jedno- i dwuprzepływowe w samolotach bojowych
    Jet turbine engine and by-pass turbojet in combat aircrafts
    Autorzy:
    Kozakiewicz, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/209996.pdf
    Data publikacji:
    2010
    Wydawca:
    Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
    Tematy:
    turbinowe silniki odrzutowe jednoprzepływowe
    dwuprzepływowe turbinowe silniki odrzutowe
    parametry jednostkowe
    parametry strumienia
    jet turbine engine
    by-pass turbojet
    parameters of individual turbine-jet engines
    parameters gas stream
    Opis:
    Artykuł przedstawia analizę parametrów jednostkowych turbinowych silników odrzutowych pod względem procesu realizowanego w tych silnikach. Zaprezentowano tendencje zmian ciągu jednostkowego i jednostkowego zużycia paliwa w zależności od roku wprowadzenia silnika do eksploatacji oraz schematy ideowe silników. Przeanalizowano przebiegi zmian obliczonych parametrów gazodynamicznych wzdłuż kanałów przepływowych turbinowych silników odrzutowych użytkowanych w lotnictwie wojskowym RP na samolotach bojowych oraz wpływ zakresu lotu na ich przebieg i zakres wartości.
    This paper presents analysis of parameters of individual turbine-jet engines in respect of the process realized in these engines. There are introduced the tendencies of changes of the specific thrust and the specific fuel consumption depending on the year of the introduction of the engine to the exploitation and schematic diagrams of engines. The courses of changes of calculated parameters along tubes of flow turbine-jet engines used in combat aircrafts are analysed and the influence of the range of the flight on their course and the range of value.
    Źródło:
    Biuletyn Wojskowej Akademii Technicznej; 2010, 59, 3; 201-217
    1234-5865
    Pojawia się w:
    Biuletyn Wojskowej Akademii Technicznej
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Aircraft fuel consumption and emissions during cruise, effect of the jet stream
    Autorzy:
    Głowacki, P.
    Kawalec, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/242826.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    turbine engine
    cruise
    jet stream
    exhaust emissions
    Opis:
    Article presents the results of fuel consumption calculation during cruise compared to remaining aircraft flight phases. Based on fuel consumption, methodology of pollutants quantitative estimation emitted by turbine engines has been developed. Material provides evaluation results of aircraft CO2, CO and NOx effusion using fuel consumption data taken from aircraft Flight Data Recorder (FDR) during cruise of various aircraft types. Knowledge of the amount of aircraft emissions on high altitudes is very important for climatologists in order to understand eventual changes in the Earth atmosphere due to aviation activities. The authors would like to draw attention of the aviation professionals to the fact that aircraft fuel consumption during cruise; thereby amount of toxic content in the exhaust from the turbine engine is significantly higher especially during flights against jet stream. Thousands flights of two operators were processed using algorithms developed by authors. The article gives an example of fuel consumption and thereby CO2, CO and NOx emission estimation based on engine performance taken from their test cell results. Calculations were performed with the consideration of the factor for engines deterioration through operation time provided by its manufacturer.
    Źródło:
    Journal of KONES; 2015, 22, 2; 63-70
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Low temperature properties of fuel mixtures of kerosene and fame type used to supply turbine engines in marine and other non-aeronautical applications
    Autorzy:
    Dzięgielewski, W.
    Gawron, B.
    Kulczycki, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/260024.pdf
    Data publikacji:
    2015
    Wydawca:
    Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
    Tematy:
    jet fuel
    biocomponents
    marine turbine engine
    low temperature properties
    Opis:
    A worldwide trend to popularise gradually increasing use of biofuels in various applications was a motivation for gaining interest in FAME as a commonly available biocomponent to fuels combusted in turbine engines. These engines are mainly used in aeronautics, but many of them are also used in other, non-aeronautical areas, including marine navigation. Specific conditions in which fuels are combusted in turbine engines used in these applications are the reason why fuel mixtures of kerosene and FAME type should reveal relevant low temperature characteristics. The article presents results of tests of low temperature properties of mixtures of the jet fuel Jet A-1 and methyl esters of higher fatty acids (FAME). The prepared mixtures contained different contents of FAME. The obtained results present changes of: viscosity, cloud point, pour point, crystallising point, and cold filter plugging point, depending on the percentage by volume of FAME. They also prove that the course of changes of low temperature properties of these mixtures is affected by chemical structure of the biocomponent.
    Źródło:
    Polish Maritime Research; 2015, 2; 101-105
    1233-2585
    Pojawia się w:
    Polish Maritime Research
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Raspredelenie kapel v processe raspylivaniâ dizelnogo topliva i ego smesi s biokomponentami
    Autorzy:
    Klyus, O.
    Labeckas, G.
    Slavinskas, S.
    Mažeika, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/906621.pdf
    Data publikacji:
    2013
    Wydawca:
    Akademia Morska w Szczecinie. Wydawnictwo AMSz
    Tematy:
    diesel engine
    fuel injector
    atomized jet
    droplet distribution
    biofuel
    Opis:
    Droplet distribution in an atomized jet of Diesel fuel and biofuel mixture
    Źródło:
    Zeszyty Naukowe Akademii Morskiej w Szczecinie; 2013, 36 (108) z. 2; 93-97
    1733-8670
    2392-0378
    Pojawia się w:
    Zeszyty Naukowe Akademii Morskiej w Szczecinie
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Combustion, performance and exhaust emissions of the diesel engine operating on jet fuel
    Autorzy:
    Labeckas, G.
    Slavinskas, S.
    Vilutiene, V.
    Powiązania:
    https://bibliotekanauki.pl/articles/248056.pdf
    Data publikacji:
    2012
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    diesel engine
    jet fuel
    autoignition
    combustion
    performance
    emissions
    smoke
    Opis:
    The article focuses on bench testing results of a four-stroke, four-cylinder, direct-injection, naturally aspirated diesel engine operating on the normal 95vol% (class C) diesel fuel + 5vol% RME (DF), F-34 jet fuel (JF) and jet fuel F-34 treated with the cetane improver (JF+0.12vol%). The purpose of the research is to investigate the availability to use of military F-34 jet fuel for land-based direct injection diesel engine powering and examine the effect of F-34 fuel and F-34 fuel treated with 0.12vol% 2-ethylhexyl nitrate on the autoignition delay, combustion, engine performance, emissions and smoke opacity of the exhausts. The peak in-cylinder gas pressure generated from JF and JF+0.12vol% is lower by 4.3% and 2.8% at 1400 min–1 speed, and 2.5% and 5.7% at 2200 min–1 speed compared to that 86.6 MPa and 82.5 MPa of the normal diesel. At rated 2200 min–1 speed, the use of treated jet fuel leads to smoother engine performance under all loads and the maximum cylinder pressure gradient lowers by 9.4% as against that 15.9 bar/deg of base diesel. The minimum brake specific fuel consumption (bsfc) for F-34 and treated F-34 fuels decreases by 4.8% and 3.5% at 1400 min–1 speed and increases by 2.7% and 3.7% at 2200 min–1 speed compared to 249.5 g/kWh and 251.8 g/kWh values of base diesel. Maximum NO emissions produced from fuels JF and JF+0.12vol% decrease by 11.5% and 7.0% at 1400 min–1, and 17.1% and 17.3% at 2200 min–1 speed compared to 1705 ppm and 1389 ppm emanating from the normal diesel. Maximum CO emissions produced from jet fuel JF and JF+0.12vol% decrease by 39.3% and 16.8% compared to that 4988 ppm produced from base diesel running at 1400 min–1 speed. At 2200 min-1 speed, the ecological effect of using fuel F-34 fuel decreases and the CO sustains over the whole load range at the same level and increases by 2.5% and 3.0% with regard to the normal diesel operating under high load. The HC emission also is lower by 78.3% and 58.8% for low and high loads compared to 230 ppm and 1820 ppm of the normal diesel running at 1400 min–1 speed. The smoke opacity ,generated from fuels JF and JF+0.12vol% sustains at lower levels over the all load range with the maximum values decreased by 14.6% and 8.1% with regard to 94.9% of the normal diesel operating at 1400 min–1 speed. The test results show that military F-34 fuel is a cleaner-burning replacement of diesel fuel and suggests fuel economy with reduced all harmful species, including NO, NO2, NOx, CO, HC, and smoke opacity of the exhausts.
    Źródło:
    Journal of KONES; 2012, 19, 1; 227-236
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A method of assessing the tendency of aviation fuels to generate thermal degradation products under the influence of high temperatures
    Autorzy:
    Sarnecki, J.
    Gawron, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/246718.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet fuel
    turbine engine
    thermal stability
    test rig
    non-standard method
    Opis:
    The subject of the article concerns the issues associated with thermal degradation of aviation fuels under high temperature conditions. Due to the intensive development towards increasingly higher thermal loads for both, turbine aviation engines, as well as the used fuels, the issue of thermal stability of the fuel itself is extremely important. In aviation, the fuel, apart from direct participation in energy generation during the combustion process of a fuel-air mixture, also takes part in the heat transfer in many aircraft systems. As a result, requirements in terms of the fuel’s thermal potential are increasingly higher. The standard method for determining the thermal stability of fuel executed on a JFTOT device proves to be insufficient in the context of the appearing issues in current operation. The article presents a non-standard approach to the assessment of aviation fuel thermal degradation with the use of a specialist test rig. The authors believe that the presented methodology and the measurement capabilities of the test rig are valuable supplementary material for the standardized thermal stability test. It allows more thoroughly understanding the phenomena undergoing in the fuel impacted by high temperatures. The article has been prepared within the research project no. 2011/01/D/ST8/06567 funded by the National Science Centre in Poland.
    Źródło:
    Journal of KONES; 2017, 24, 4; 377-384
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The effect of aviation fuel JP-8 and diesel fuel blends on engine performance and exhaust emissions
    Autorzy:
    Labeckas, G.
    Slavinskas, S.
    Vilutienė, V.
    Powiązania:
    https://bibliotekanauki.pl/articles/949492.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    diesel engine
    jet fuel
    diesel fuel
    autoignition
    combustion
    performance
    exhaust emissions
    Opis:
    The article presents bench test results of a four-stroke, four-cylinder, naturally aspirated, DI diesel engine operating with neat JP-8 fuel (J) and its blends with Diesel fuel (D) in following proportions by volume: 90/10 (J+10D), 70/30 (J+D30), 50/ 50 (J+D50), 30/70 (J+D70), and 100% diesel fuel (DF). The purpose of the research was to analyse and compare changes occurred in the autoignition delay, combustion events, engine performance efficiency, emissions, and smoke of the exhaust when running on JP-8 fuel, jet-diesel fuel blends, and diesel fuel at a full (100%) engine load and speed of 1400 min–1 at which maximum torque occurs and rated speed of 2200 min–1. It was found that the start of injection (SOI) and the start of combustion (SOC) occurred earlier in an engine cycle and the autoignition delay decreased by 9.0% and 12.7% due to replacement of aviation JP-8 fuel with diesel fuel at a full load and the latter speeds. Maximum in-cylinder pressure was 6.8% and 4.0% higher when operating with diesel fuel, whereas brake thermal efficiency was 3.3% and 7.7% higher, and brake specific fuel consumption 2.8% and 7.0% lower when using fuel blend J+D50 compared with the respective values measured with neat JP-8 fuel. Emissions of nitric oxide (NO) and nitrogen oxides (NOx) were 13.3% and 13.1% higher from a straight diesel running at speed of 1400 min–1, and 19.0% and 19.5% higher at a higher speed of 2200 min–1. The carbon monoxide (CO) emissions and total unburned hydrocarbons (HC) decreased 2.1 times and by 12.3% when running with fuel blend J+D70 at speed of 2200 min–1 compared with those values measured with jet fuel. Smoke of the exhaust was 53.1% and 1.9% higher when using fuel blend J+D10 than that of 46.9% and 70.0% measured with jet fuel at speeds of 1400 and 2200 min–1. The engine produced 34.5% more smoke from combustion of fuel blend J+D70 at the low speed of 1400 min–1, but smoke converted to be 11.3% lower when operating at a higher speed of 2200 min–1.
    Źródło:
    Journal of KONES; 2015, 22, 2; 129-138
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Tests of a prototype spark-ignited, direct-injection engine powered by JET-A1 fuel
    Autorzy:
    Świątek, Piotr
    Fuć, Paweł
    Ziółkowski, Andrzej
    Świątek, Lech
    Melwiński, Paweł
    Powiązania:
    https://bibliotekanauki.pl/articles/133682.pdf
    Data publikacji:
    2019
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    alternative fuel
    test engine
    piston aircraft engine
    jet-a1
    paliwo alternatywne
    silnik testowy
    tłokowy silnik lotniczy
    Opis:
    The article presents a part of the work done in a research and development project being made by SWIATEK Lech Swiatek company. It describes the comparison of different fuels used in piston engines with JET-A1 turbine engine fuel. Next, the proposed combustion process of JET-A1 fuel and a prototype one-cylinder engine are described. In details, a special cylinder head and direct injection programmable computer are presented. In the next part, a designed and built test stand is described. Finally, the results and conclusions are presented. The designed test stand enabled to perform assumed tests. The innovative JET-A1 combustion process was possible to perform and the power and torque were higher in 1900-3000 rpm range than with the gasoline fuel. The designed GDI programmable injection computer enabled to fully control the injection and ignition parameters.
    Źródło:
    Combustion Engines; 2019, 58, 3; 117-120
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The study of the continuously rotating detonation combustion chamber supplied with different types of fuel
    Autorzy:
    Łukasik, B.
    Czyż, S.
    Irzycki, A.
    Rowiński, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/246684.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    rotating detonation
    air/Jet-A detonation
    detonation combustion chamber
    internal combustion engine
    Opis:
    The paper summarizes research that was conducted last year as part of the project of “Turbine engine with detonation combustion chamber”. In this project, throughout 2012 and early 2013, tests were carried out on a test stand connected to the compressed air system. Research, of the rotating detonation phenomena, was carried out for a number of detonation chambers with different interior channel geometry. In addition, for each geometry configuration, tests were carried out for different levels of choking of the chamber outlet and hence for different pressures conditions inside the detonation chamber. This article presents the results of tests carried out for gaseous (hydrogen), hybrid (hydrogen + kerosene) and liquid (Jet-A) fuels, using different types of fuel injectors and for different fuel injection configuration settings (inside the chamber, or in front of the chamber). During these tests, parameters such as pressure behind the detonation wave (using piezoelectric sensors), the static pressure in front of and inside the detonation chamber and temperature: before, inside and at the outlet of the chamber, were measured. Research was performed for the various mass flow rates of air and fuel injected into the chamber that means for the different air-fuel equivalence ratios (Lambda). The main achievement of this study was to obtain a stable and reproducible rotating detonation of air and heated kerosene (Jet-A) mixture, thus the results presented in this paper presents mainly these tests as the most interesting to the reader
    Źródło:
    Journal of KONES; 2013, 20, 3; 259-266
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Modyfikowanie własności smarnych olejów stosowanych w silniku odrzutowym oraz w układach sterowania lotem
    Modifying the lubricating properties of oils used in jet engines and flight control systems
    Autorzy:
    Laber, S.
    Laber, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/189203.pdf
    Data publikacji:
    2015
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    samoloty odrzutowe
    olej silnikowy
    olej hydrauliczny
    własności smarne
    jet aircraft
    engine oil
    hydraulic oil
    lubricating properties
    Opis:
    W artykule przedstawiono problemy smarowania silników oraz rodzaje środków smarowych stosowanych w silnikach odrzutowych. Przedstawiono wyniki badań własności smarnych: obciążenie zespawania Pz, wskaźnik zużycia pod obciążeniem Ih, obciążenie niezacierające Pn, obciążenie zacierające Pt oraz graniczne obciążenie zużycia Goz badanych środków smarowych handlowych oraz modyfikowanych preparatem eksploatacyjnym (PE) o działaniu chemicznym Motor Life Professional. Badania wykazały, że dodanie preparatu eksploatacyjnego w ilości 5% w stosunku objętościowym wpłynęło na poprawę własności przeciwzużyciowych i przeciwzatarciowych badanych środków smarowych.
    The article presents the problems of lubrication and types of lubricants used in jet engines. The results of tribological properties were presented: weld point Pz, load-wear index Ih, last nonseizure load Pn, seizure load Pt, limiting load of wear Goz for commercial oils and these oils with Motor Life Professional addition. Studies have shown that the addition of additive in an amount of 5% by volume has improved antiwear and antiseizure properties investigated lubricants.
    Źródło:
    Tribologia; 2015, 5; 79-88
    0208-7774
    Pojawia się w:
    Tribologia
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Heavy fuel engines
    Silniki ZI zasilane paliwem lotniczym
    Autorzy:
    Dutczak, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/133949.pdf
    Data publikacji:
    2015
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    drones
    unmanned aerial vehicle
    UAV
    aviation kerosene
    SI engine
    Jet A
    JP-5
    JP-8
    heavy fuel engines
    HFE
    drony
    nafta lotnicza
    silnik ZI
    Opis:
    The principle of operation and chosen examples of construction of SI engines designed to be powered with aviation fuel (Heavy Fuel Engines – HFE) have been presented in the article. Contemporary solutions of the HFE combustion system constitute the further development of a patent of an Australian company Orbital working in the field of two-stroke SI engines. Engines of this type, characterized by low weight and low value of specific fuel consumption, are used among others for the propulsion of drones (Unmanned Aerial Vehicles – UAV), where range and endurance are essential parameters. That is also a practical realization of the military logistical concept of using a "single fuel in the battlefield".
    W artykule przedstawiono zasadę działania silników z zapłonem iskrowym i wybrane przykłady konstrukcji tych silników przewidzianych do zasilania paliwem lotniczym na bazie nafty, tzw. HFE (Heavy Fuel Engines). Współczesne rozwiązania systemu spalania HFE stanowią rozwinięcie patentu znanej australijskiej firmy Orbital zajmującej się silnikami dwusuwowymi ZI. Silniki tego typu, charakteryzujące się małą masą i małą wartością jednostkowego zużycia paliwa, stosowane są między innymi do napędu współczesnych dronów, gdzie istotnymi parametrami są zasięg i długotrwałość lotu. System ten wykorzystywany jest również do realizacji wojskowej logistycznej koncepcji stosowania jednego typu paliwa do wszystkich pojazdów.
    Źródło:
    Combustion Engines; 2015, 54, 4; 34-46
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
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