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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:
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:
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:
Laser ablation cleaning of the aeronautical jet engine turbine paddles
Autorzy:
Napadłek, W.
Trawiński, G.
Powiązania:
https://bibliotekanauki.pl/articles/247794.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
nickel based ŻS6K- Wl alloy
aeronautical engine paddle
laser ablation cleaning
surface layer topography
Opis:
Preliminary results ablation of the laser cleaning was introduced in the article elements of the turbine engine of airplane (blades, guide rings, the chambers of oxidising). Cleaning of these units was realized to obtainment of the metallically fine superficial layer for the chosen melts of Fe - C and on the datum feature Nor, prepare to the processes welds or the spraying thermal of coating barriers thermal TBCS. The chosen results of the selection of parameters were introduced in the support about steorology and the cleanness of the superficial layer. Various parameters: laser radiation power density, impulse duration, the frequency control and the laser spot lap stage were applied in laboratory experiments. Laser radiation influence effects were estimated on the surface photo, microstructure, chemical composition in microzones investigation basis. The stereoscopic microscopy, electron scanning microscopy (SEM) and the X-ray analysis were used in investigations. Very good cleaning effects are from oxides, accumulations of turbine blades. In particular, studied elements of aircraft turbine engine, characteristic surface and area topography of heat resistant nickel alloy, tests results of chemical constitution in the characteristic micro-zones of surface layer of high-temperature creep are presented in the paper.
Źródło:
Journal of KONES; 2010, 17, 4; 369-375
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
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:
Theoretical studies of variable geometry : hot section of the miniature jet engine
Autorzy:
Chmielewski, M.
Fulara, S.
Gieras, M.
Powiązania:
https://bibliotekanauki.pl/articles/243769.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
small gas turbine
variable geometry
combustor chamber
turbine nozzle
efficiency
Opis:
The aim of this article is to present the results of theoretical studies regarding the use of variable geometry hot section of a miniature gas turbine. The variable geometry combustor and variable area nozzle concepts for GTM-120 miniature jet engine are presented in particular. Recent trends of propulsion system size reduction, low-emission combustion and improved fuel efficiency have been considered. A system of variable geometry combustor and variable area nozzle has been proposed as solution. The basic zero-dimensional analytical models for variable geometry combustor and variable area nozzle are developed. Chemkin based model shows significant NOX/CO emissions reduction and combustor outlet enthalpy increases with the use of variable geometry combustor chamber. The analytical model of the variable area nozzle has been proposed. It shows turbine effectiveness increase across its operating range by raising the compressor working line. As a result, noticeable turbine stage efficiency increase has been obtained. Finally, physical implications and future work plans regarding variable geometry hot section of miniature gas turbines are discussed.
Źródło:
Journal of KONES; 2016, 23, 2; 69-80
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
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:
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:
A brief overview and metallography for commonly used materials in aero jet engine construction
Autorzy:
Belan, J.
Vasko, A.
Kucharikova, L.
Powiązania:
https://bibliotekanauki.pl/articles/111670.pdf
Data publikacji:
2017
Wydawca:
Stowarzyszenie Menedżerów Jakości i Produkcji
Tematy:
aluminium alloy
titanium alloy
nickel-base alloys
metallography procedures
B/W and colour contrast
stop aluminium
stop tytanu
stopy na bazie niklu
odczynnik trawiący
Opis:
Aluminium, titanium, and nickel base alloys are mostly and widely used for aircraft jet engine construction. A proper evaluation of its microstructure is important from working safety point of view. To receive a well prepared sample of microstructure, some important steps have to be undertaken. Except for proper grinding and polishing of a sample, structure developing is a significant step, too. In order to develop microstructure various chemical reagents were used to achieve the best results for microstructure evaluation. The chemical reagents were used according to the previous knowledge and some new ones were also tested. Aluminium AK4-1č, titanium VT – 8, and nickel VŽL – 14 and ŽS6 – U alloys were used as an experimental materials. Alloy AK4-1č is used for fan blade production with working temperatures up to 300°C. It is a forged piece of metal machined down into final shape by five-axe milling machine. Alloy VT – 8 is used for high pressure compressor rotor blade production with working temperatures up to 500°C. Blades are forged as well and finally grinded. Finally nickel base alloys VŽL – 14 and ŽS6 – U are used for turbine blade production with working temperatures up 950°C. Blades for turbine are casted into mould with reducible models.
Źródło:
Production Engineering Archives; 2017, 17; 9-14
2353-5156
2353-7779
Pojawia się w:
Production Engineering Archives
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of the wind dependent duration of the cruise phase on jet engine exhaust emissions
Autorzy:
Pawlak, M.
Kuźniar, M.
Powiązania:
https://bibliotekanauki.pl/articles/245313.pdf
Data publikacji:
2018
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
air transport
jet engines
air pollution
emission
exhausts
wind impact
Opis:
Nowadays more and more attention is paid to minimizing the costs of air operations. The largest share in the cost of the flight is the cost of consumed fuel. Taking into account the external conditions, having impact on the aircraft, such as wind direction and magnitude when planning the aircraft trajectory it is possible to reduce flight time and thus reduce fuel consumption. An additional advantage is the simultaneous reduction of pollutants in the jet engines exhausts. In the times of pro-ecological trends and concepts (e.g. Clean Sky, Single European Sky, CORSIA) this aspect is of crucial importance. The emission of selected pollutants in the jet engine exhausts (NOx, CO and HC) emitted during the flight of a business jet on the route whose cruise phase was assumed 1000 km long was determined in the article. The aircraft used in the research was Gulfstream GIV, powered by two Rolls Royce TAY 611-C engines, for which a cruising altitude of 10 km and a flight speed of 0.8 Ma were assumed. The thrust necessary for the flight at these cruise parameters was set, and then the engine thrust appropriate for the flight and the corresponding specific fuel consumption were determined. On this basis, based on the available ICAO data, the emission of selected pollutants in tis engines exhausts was determined for windless conditions. Next, the analysis of the impact of wind - its magnitude and direction – on the emission of these pollutants was made. The results of the conducted analyses are presented in diagrams and discussed in the conclusions.
Źródło:
Journal of KONES; 2018, 25, 3; 371-376
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:
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:
Identyfikacja stanu dynamicznego turbinowych silników lotniczych
Identification of dynamic state of the airplane turbine jet engine
Autorzy:
Żółtowski, B.
Powiązania:
https://bibliotekanauki.pl/articles/327912.pdf
Data publikacji:
2001
Wydawca:
Polska Akademia Nauk. Polskie Towarzystwo Diagnostyki Technicznej PAN
Tematy:
diagnostyka techniczna
identyfikacja
silnik lotniczy
eksploatacja
airplane engine
technical diagnostics
identification
exploitation
Opis:
W pracy tej przedstawiono zasady modelowania w identyfikacji stanu dynamicznego maszyn. Wskazano na możliwe sposoby modelowania stanu dla potrzeb diagnostyki technicznej. Jako przykład omówiono badania wstępne silników turbinowych, które pozwalają na ocenę i prognozowanie ich stanu technicznego oraz ustalenie polityki eksploatacyjnej silników, co jest bardzo istotne z punktu widzenia bezpieczeństwa i rachunku ekonomicznego.
In this work one represented rules of fashioning identification state of dynamic machines. One showed on possible manners of fashioning of state for needs of technical diagnostics. As example one talk overed investigations initial reliabilities of turbine - engines, which permit on estimation and prognoses their of technical state and settlement of policy exploitation of engines, what is very essential from point of view safety and of economic bill.
Źródło:
Diagnostyka; 2001, 24; 23-30
1641-6414
2449-5220
Pojawia się w:
Diagnostyka
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:
Determination of the Geometric Properties of a Jet Engine Fan Blades Based on Modal Vibration Testing
Autorzy:
Osiewicz, Maciej
Cieślak, Sławomir
Bielecki, Marcin
Powiązania:
https://bibliotekanauki.pl/articles/36778970.pdf
Data publikacji:
2022
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
blade vibration
modal analysis
finite elements
design
aviation
Opis:
The article presents an experimental method of determining the geometric properties of jet engine rotor airfoils based on modal vibration testing. The procedure is based on adjusting the results of analytical calculations to the laboratory outcomes. Experimental tests were carried out on a set of 20 jet engine fan blades made of AL7022-T6 aluminium alloy. Each blade differed in weight and geometric dimensions within the accepted design tolerance. Numerical analysis of five airfoils that differed in thickness was performed. Modal vibration test results were summarised and compared with the results obtained by the numerical method. The comparison revealed a high similarity of the frequency and form of vibrations acquired by numerical simulation for each of the blades in relation to the executed vibration testing. Based on the verification of the theoretical model with the results obtained through experimental testing, conclusions were drawn about the object’s dynamic behaviour and its technological quality and geometric properties, whereby each of airfoil was probably thinned.
Źródło:
Transactions on Aerospace Research; 2022, 3 (268); 56-74
0509-6669
2545-2835
Pojawia się w:
Transactions on Aerospace Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of 1st stage compressor rotor blade stress and vibration amplitudes in one-pass jet engine
Autorzy:
Szczepanik, R.
Powiązania:
https://bibliotekanauki.pl/articles/244813.pdf
Data publikacji:
2013
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
diagnostics of aircraft engines
compressor blade dynamics
Opis:
This paper considers 1st stage compressor blade dynamics in the one-pass jet engines of trainer aircraft. Research was carried out on an engine test bench using the SAD system and its results were compared with those obtained using the tensometric approach. In this paper presented basic dynamic properties of rotor blades, bench test of rotor blade dynamics, Bench tests of the dynamic behaviour of blades subjected to external impacts and then Comparison of strain gauge and SAD tip-timing results. Then discusses the results of tests assessing the accuracy of the 1987 ITWL device by comparing strain gauge signals with those recorded by SAD apparatus in a running engine. It also presented simultaneous vibration readings of all the rotor blades at selected rotation speeds. Also shows that increased stress in these blades may be due to repeated engine surges, normal and hot engine surges, entry into the engine of a foreign object. Among others selection and layout of rotor blades in the 1st stage of a one-pass engine compressor, stress amplitudes for rotor blade, stress in rotor blade, stress amplitudes, free inlet flow and smooth engine acceleration, vibration amplitudes, asynchronous vibrations are presented in the paper.
Źródło:
Journal of KONES; 2013, 20, 4; 441-450
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:
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:
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:
A new diagnosing method of the internal structure of the titanium fan of a jet engine with laser ultrasonics
Autorzy:
Swornowski, P.
Powiązania:
https://bibliotekanauki.pl/articles/221783.pdf
Data publikacji:
2011
Wydawca:
Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:
non-destructive testing (NDT)
laser ultrasonic
titanium fan
aerospace
Opis:
Advanced metallic material processes (titanium) are used or developed for the production of heavily loaded flying components (in fan blade construction). The article presents one process for diagnosing the blade interior by means of laser ultrasonography. The inspection of these parts, which are mainly made of titanium, requires the determination of the percentage of bonded grain sizes from around 10 to 30 žm. This is primarily due to the advantages of a high signal-to-noise ratio and good detection sensitivity. The results of the research into the internal blade structure are attached.
Źródło:
Metrology and Measurement Systems; 2011, 18, 3; 441-451
0860-8229
Pojawia się w:
Metrology and Measurement Systems
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:
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:
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:
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:
Optimization of a Jet Engine Compressor Disc with Application of Artificial Neural Networks for Calculations Related to Time and Mass
Autorzy:
Kieszek, Rafał
Kozakiewicz, Adam
Rogólski, Robert
Powiązania:
https://bibliotekanauki.pl/articles/2023846.pdf
Data publikacji:
2021
Wydawca:
Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:
optimization
artificial neural networks
axial compressors
turbine jet engines
aerospace engineering
Opis:
The paper presents the results of a series of numerical research on the possibility of applying Artificial Neural Networks (ANNs) for ultimate strength calculations of selected parts of rotating machines. The layout and the principle of the algorithm operation were described, beginning from the general assumptions and then moving to the detailed description of the subsequent modules. The effects of applying the algorithm were presented on the example of the analysis of the compressor disc. The significant benefits of using it were the reduction of optimization time by about 40% and the disc weight reduction by 0.5 kg. Accuracy of ANNs was different in each iteration of a presented algorithm. Finally, high accuracy of neural networks was achieved with the following mean values of relevant indices reached in the last iteration: RMSE=0.5983, MAPA=0.0733 and R^2=0.99895. The further perspectives of undertaken research were defined at the end.
Źródło:
Advances in Science and Technology. Research Journal; 2021, 15, 2; 208-218
2299-8624
Pojawia się w:
Advances in Science and Technology. Research Journal
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-25 z 92

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