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Wyszukujesz frazę "jet engine" wg kryterium: Wszystkie pola


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

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