Temat: aircraft engines - Katalog OPAC zbiorów

Skocz do pozycji: 31.

Tytuł:: A methodology of unsteady investigations of helicopter airfoils
Metodyka niestacjonarnych badań profili śmigłowcowych
Autorzy:: Krzysiak, A.
Ruchała, P.
Powiązania:: https://bibliotekanauki.pl/articles/213106.pdf
Data publikacji:: 2010
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: silniki i paliwa lotnicze
aerodynamika i mechanika lotu
materiałoznawstwo
aircraft engines and fuels
aerodynamics and mechanics of flight
materials science
Opis:: The paper describes amethodology of unsteady experimental investigations of helicopter airfoils. It has been implemented during tests of helicopter airfoil, carried out in Aerodynamics Department of Institute of Aviation for PZL-Świdnik and Ministry of Science and Higher Education (MNiSW – Ministerstwo Nauki i Szkolnictwa Wyższego) as a part of grant: “Development and deployment of new generation of design, technological and material solutions for main rotor and airframe elements of PZL W-3A Sokół helicopter”. The tests have aimed to modeling (in the wind tunnel) the dynamic stall phenomena incidence, which may appear on main rotor blades during forward flight. It causes a strong vibration of blades, thus defining a considerable limit of helicopters’ performance. The dynamic stall phenomena is caused by fast angle of attack transition, which appears during forward flight. A similar transition on tested model was evoked by its oscillations with requested amplitude and frequency. The mechanism causing the oscillations of model and the measurement equipment have been described further. The discussed methodology covers pressure distribution measurements, basing on measurement of local static pressure on the surface of respectively adapted model. Because the measurements of pressure are not simultaneous, the pressure coefficient distribution (as a function of time and angle of attack) has been approximated using Fourier series. The coefficients of lift and pitching moment have been calculated as a result of integration the pressure coefficient distribution. An algorithm of calculation has been described also.
Praca opisuje metodykę eksperymentalnych niestacjonarnych badań ciśnieniowych, dotyczących śmigłowcowych profili aerodynamicznych. Została ona wdrożona w trakcie badań profilu śmigłowcowego, wykonanych w Zakładzie Aerodynamiki Instytutu Lotnictwa dla PZL Świdnik i Ministerstwa Nauki i Szkolnictwa Wyższego (w ramach projektu celowego „Opracowanie i wdrożenie nowej generacji rozwiązań konstrukcyjnych, technologicznych i materiałowych dla wirnika nośnego i elementów płatowca śmigłowca PZL W-3A Sokół”. Celem tego typu badań jest modelowanie wwarunkach tunelowych zjawiska tzw. przeciągnięcia dynamicznego, które może wystąpić na łopatach wirnika nośnego śmigłowca w czasie lotu postępowego. Powoduje ono silne drgania łopat, wobec czego stanowi istotne ograniczenie osiągów śmigłowców. Zjawisko przeciągnięcia dynamicznego jest związane z szybką zmianą kąta natarcia, jaka występuje wczasie lotu postępowego śmigłowca. Warunki te odwzorowano za pomocą modelu wykonującego ruch oscylujący o zadanej częstotliwości i amplitudzie. Mechanizm wywołujący oscylacje, jak również użyta aparatura pomiarowa, zostały opisane w pracy.
Źródło:: Prace Instytutu Lotnictwa; 2010, 5 (207); 32-47
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 32.

Tytuł:: Areas of Investigation into Air Intake Systems for the Impact on Compressor Performance Stability in Aircraft Turbine Engines
Autorzy:: Kozakiewicz, Adam
Adamczyk, Maciej
Wróblewski, Mirosław
Powiązania:: https://bibliotekanauki.pl/articles/2067549.pdf
Data publikacji:: 2022
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:: mechanical engineering
aviation
aircraft engines
compressor stall
compressors
Opis:: The high demands placed on aircraft turbine engines necessitate the use of the latest engine compressors which must be increasingly efficient and more robust due to the increased loads. The key safety issue in this context is to ensure compressor stability over all engine speed ranges and aircraft flight regimes. This paper presents selected areas of research into surge and stall of axial compressors used in aircraft turbine engines based on scientific publications in recent years. On the basis of the analysed literature the authors defined the main research areas into compressor surge, namely: air intake research, compressor research and combined air intake and compressor system research. On the background of the conducted analysis the authors has presented their own areas of research. The aim of this work is to search for an intake-compressor design more passively resistant to stall or surge phenomena without necessity of implementation of complex control systems to prevent compressor stall.
Źródło:: Advances in Science and Technology. Research Journal; 2022, 16, 1; 62--74
2299-8624
Pojawia się w:: Advances in Science and Technology. Research Journal
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 33.

Tytuł:: Determination of Ranges of Unstable Operation of Axial Compressor for Aircraft Turbine Engines
Wyznaczanie zakresów niestatecznej pracy sprężarki osiowej lotniczych silników turbinowych
Autorzy:: Kozakiewicz, Adam
Adamczyk, Maciej
Majcher, Maciej
Powiązania:: https://bibliotekanauki.pl/articles/2073829.pdf
Data publikacji:: 2022
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: mechanical engineering
aviation
aircraft engines
stall
compressor
inżynieria mechaniczna
lotnictwo
silniki lotnicze
pompaż
sprężarki
Opis:: Currently, strict requirements are set for aircraft turbine engine performance, which requires introducing larger, more complex, and more loaded compressors. In sub-assemblies designed in this manner, a vital challenge is to maintain stable compressor operation across wide range of operating conditions. This article presents the results of analysis and estimation of the range of unstable operation of an example axial compressor for a turbofan jet engine with high mass flow ratio. The analyses and numerical simulations performed made it possible to estimate the limit performance for compressor operation for two particularly important phases of flight.
Współcześnie stawia się wysokie wymagania wobec parametrów osiąganych przez lotnicze silniku turbinowe, co powoduje konieczność wprowadzania do konstrukcji coraz większych, bardziej skomplikowanych i obciążonych sprężarek. W tak projektowanych podzespołach istotnym wyzwaniem jest zachowanie stabilności pracy sprężarki w szerokim zakresie warunków operacyjnych. W niniejszym artykule przedstawiono wyniki analizy i oszacowania zakresu niestatecznej pracy przykładowej sprężarki osiowej do dwuprzepływowego silnika turbinowego o dużym stopniu podziału masowego natężenia przepływu. Przeprowadzone analizy i obliczenia pozwoliły na oszacowanie granicznych parametrów pracy sprężarki dla dwóch szczególnie istotnych faz lotu samolotu.
Źródło:: Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa; 2022, 13, 1 (47); 45--56
2081-5891
Pojawia się w:: Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 34.

Tytuł:: Analysis of an aircraft engine start-up process on the example of the PZL-130 TC-II „Orlik” training aircraft
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/244355.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
qualification tests of aircraft driving units
Opis:: The paper discloses the analysis of processes that take place during the start-up operation of the driving unit for the training aircraft of the TZL-130 TC-II Turbo-Orlik type. The aircraft is designed for selective and initial trainings at the Air Force School of “Little Eagles” in Dęblin. The driving unit comprises the PT6A-25C turbo-propeller engine from Pratt & Whitney combined with the four-bladed airscrew from Hatzell. It is specifically mentioned that data for the analysis were sourced from the S2-3a on-board recorder of flight parameters manufactured by the Air Force Institute of Technology (AFIT). The analysis was carried out both during ground and flight tests. The paper briefly outlines general structures and operation principles of typical start-up systems with the focus to their key components. Attention is paid to how important it is to select an appropriate start-up system to match the specific aircraft type and the guideline parameters for selection that should be adhered to are specified. Also there are disclosed the key mathematical relationships that are indispensable to design start-up systems and to find out their basic characteristics. It is emphasized that the start-up operation must be considered as a non-stationary process that lasts from the standstill state of the engine until the moment when the minimum required rpm is reached, sufficient to generate necessary power of the engine. In addition, the attention is paid to the fact that the value of the engine acceleration is crucial to the achievable start-up time that is deemed as one of key parameters for all start-up systems. It is demonstrated that to achieve the required level of acceleration, it is necessary to secure the so called overhead of the engine power which needs constant flow offuel and air into the combustion chamber of the engine. The last part of the paper comprises selected characteristic curves that were obtained from the analysis of the engine start-up processes both on ground and in flight. The final conclusions emphasize that the start-up system for the presented driving unit is really efficient and guarantees correct operation of the engine under any conditions.
Źródło:: Journal of KONES; 2014, 21, 3; 177-189
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 35.

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

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Skocz do pozycji: 36.

Tytuł:: Use of data from on-board data recorders for acceptance tests of avionic driving units
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/243070.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
qualification tests for avionic driving units
Opis:: The paper explains how information stored in on-board recorders of flight parameters can be used for acceptance tests, also referred to as qualification tests. The disclosed example refers to the An-28 ‘Bryza’ aircraft where an old airscrew was substituted with the new generation Hartzell airscrew of the HC-B5 MP-3D type. The airscrew is an integral part of the driving system for the airscrew propelled aircraft that is provided with the TWD-10B engine. After revamping of the airscrew, the aircraft was named as TWD-10B/PZL-10S. The follow-up investigations were carried out with the aim to find out how much the airscrew substitution affected the alteration of key performance characteristics achieved by the driving unit of the aircraft. The investigations comprised both ground and in-flight tests and have led to determination of the essential characteristics for the engine operation as well as variations of the operational parameters in time. In some cases also so called phase portraits were found out for parameters of the engine operation so that to reflect dynamic properties of the engines. Such investigations are indispensable since the aircrafts are subject to operational limitations and technical conditions that must be mandatory fulfilled due to requirements of flight safety. The paper demonstrates that the data stored in on-board recorders of flight parameters can be really useful for execution of such acceptance (qualification) tests.
Źródło:: Journal of KONES; 2013, 20, 2; 201-206
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 37.

Tytuł:: Zastosowanie inżynierii odwrotnej do modelowania wlotu silnika samolotu wielozadaniowego na potrzeby badań przepływowych
Application of reverse engineering method to model combat aircraft aeroengines inlet for flow research purposes
Autorzy:: Kachel, S.
Kozakiewicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/208496.pdf
Data publikacji:: 2012
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: konstrukcje lotnicze
inżynieria odwrotna
parametryczne modelowanie bryły samolotu
kanały wlotowe lotniczych silników turbinowych
air constructions
reverse engineering
parametric modelling of the solid of the aircraft
intake-tubes of air-turbine engines
Opis:: W pracy przedstawiono metodę rozwiązania zagadnienia modelowania geometrii fizycznych obiektów metodą inżynierii odwrotnej, która w dużej mierze wykorzystuje nowoczesne systemy projektowania oraz pomiarów współrzędnych punktów stanowiących bazę do opisu wirtualnego modelu. Zaprezentowano metodę parametrycznego opisu geometrii odtwarzanego obiektu, wykorzystując opracowane programy w języku GRIP (dla systemu CAD/CAM/CAE Unigraphics) na bazie teoretycznych rozważań. Zasygnalizowano problem analizy błędów pomiarowych punktów z precyzyjnych pomiarów współrzędnościowych, który może być rozwiązany poprzez zastosowanie analizy odchyłek wzorzec-pomiar. Zaprezentowano metodę wyznaczenia funkcji opisujących bazowe krzywe modelowanych zespołów samolotu.
This paper is to present the solution method for the problem of modelling object's physical geometry using reverse engineering method, which in large measure relies on modern designing systems and points' coordinates measurement constituting the base for the virtual model description. Also, this is to present the reconstructed object’s parametric geometry description method using software developed in the GRIP programming language (for the system CAD/CAM/CAE Unigraphics) on the basis of theoretical considerations. The paper signals the problem of incorrect measuring points' analysis based on precise coordination measurement which can be solved by the application of deviations' standard-measurement analysis. There is presented the method of defining functions describing the base curves of modeled plane units.
Źródło:: Biuletyn Wojskowej Akademii Technicznej; 2012, 61, 2; 311-330
1234-5865
Pojawia się w:: Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 38.

Tytuł:: Reduction emission level of harmful components exhaust gases by means of control of parameters influencing on spraying process of biofuel components for aircraft engines
Autorzy:: Jankowski, A.
Powiązania:: https://bibliotekanauki.pl/articles/245547.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft engines
alternative fuels
fuel atomization
exhaust gas emissions
Opis:: The aim of the research is to test the fuel additives which decrease dimensions of atomised fuel drops, by applying changes to the specific parameters which impact the atomisation process. Those parameters include density, surface tension, viscosity and the viscosity index. Dimensions of drops of biofuels are much bigger compared to hydrocarbon fuels. By modifying the physical and chemical parameters of biofuels, dimensions of drops in an atomised fuel stream should become smaller. Those dimensions play a major role for the level of emissions of hydrocarbon and carbon monoxide, as well as mainly nitrogen oxides and particulates. The research on emissions of toxic components of fuel is relatively advanced today in the field of piston combustion engines, especially for use in car vehicles. However, the dynamic development of the air transport brings more pressure on the issue of toxic emissions in the case of aircraft engines. The level of toxic emissions from aircraft engines may be from ten up to even several thousand times greater than the level of emissions from piston engines. The issue of how biofuel additives can affect the process of fuel atomisation and thus enable the control over the atomisation to obtain the smallest possible drops leading to reduced nitrogen oxides emissions is a new and original issue. The reduced nitrogen oxides emissions in the case of biofuels is of utmost significance because, according to latest knowledge, those levels are increasing.
Źródło:: Journal of KONES; 2011, 18, 3; 129-134
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 39.

Tytuł:: Analysis of chosen fuels influence on turboprop engine work performance
Autorzy:: Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/244996.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engineering
fuel
oil
lubrication
engines
Opis:: The analysis of work parameters of a turboprop engine fuelled by various fuels was done in the paper. The turboprop engine model was presented in the beginning. The main feature of this model is description of the flow in the engine as semi-perfect gas model. By the way, the change of fumes chemical composition influence the gas properties as heat constant and isentropic index are determined. Next energy balance of a compressor and turbine was analysed and turbine pressure drop was evaluated. Finally, engine output power was determined. It was done for selected fuels, which could be applied in the aero engines. The results of analyse were presented in the tables and charts and discussed. Summary of the test results with the results for contemporary applied fuel allows drawing the conclusions about the turboprop engine performance change by various fuel application. Main of them refers to the point that higher combustion heat value of fuel and higher heat constant of fumes cause better engine work conditions By this way the hydrogen seems to be perspective fuel of future, because its combustion heat value is three times JET A-1 and by this way it is possible the engine fuel consumption will be lower.
Źródło:: Journal of KONES; 2016, 23, 2; 163-170
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 40.

Tytuł:: Analysis of thermodynamic cycle influence of turbofan mixer engine on its performance
Autorzy:: Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/245722.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
turbojet engines
modelling of turbojet engines
turbojet engine characteristics
Opis:: The turbofan engines are widely used as propulsion of the contemporary airplanes. In the military application the turbofan mixer engines are used. Although the turbofan mixer engines are applied for a long time, the information about exact analysis of their thermodynamic cycle and performance are still in complete. The thermodynamic cycle of the turbofan mixer engine is presented and discussed in this paper. Based on it the cycle parameters selection is discussed. Then the optimization of turbofan mixer engine cycle is presented. Final results present the influence of chosen engine cycle parameters on the engine performance. The results are analyzed and discussed. On the basis of them the conclusions are formulated. It is not such an easy process to choose for the turbofan mixer engine thermodynamic parameters. It is connected with the fulfilment of two important rules. The equalization of total pressure of mixer inflow streamfor mixer efficient work is the first of it. The other rule is connected with engine cycle optimization. As it is shown it is not possible to choose engine parameters to reconcile the demands of specific thrust maximization and specific fuel consumption minimization. The engine thermodynamics parameters selection process is the search of the compromise between these two demand fulfilments, very often including engine mass analysis.
Źródło:: Journal of KONES; 2009, 16, 4; 171-178
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 41.

Tytuł:: Comparison of internal processes effectiveness change influence the turbofan with and without mixer model sensitivity
Porównanie wrażliwości modelu silnika dwuprzepływowego z mieszalnikiem i bez mieszalnika na zmianę efektywności procesów wewnętrznych
Autorzy:: Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/247564.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: silniki lotnicze
silniki odrzutowe
modelowanie silników odrzutowych
charakterystyki silnika odrzutowego
aircraft engines
turbojet engines
modelling of turbojet engines
turbojet engine characteristics
Opis:: At the present time one of the way of the aircraft engines improvement is the fuel consumption reduction but the thrust should stay on the same level. One of the ways to realize this is the engine internal processes improvement. Nowadays technology and the commuter design methods allows us produce more efficient compressors, fans, turbines etc. To manage the proper process of engine improvement, it is demand to know how the chosen elements improvement influences the engine work parameters. This knowledge allows us to calculate the cost, and evaluate the effects of the improvements. In the paper, the analyzes of chosen internal engine process improvement influence on the specific thrust and the specific fuel consumption is done for turbofan engine. The processes effectives are characterized by flow losses coefficients and the processes efficiencies. In the beginning the two types of turbofan engine wit and without mixer is described. The main differences in the engines model are presented. Then the process effectiveness coefficients are defined and research method is presented. The analysis, based on the small deviation methods is use to calculate the results of the work. Then the results are presented as comparison graphs for the engine with the mixer and without the mixer. The results are analyzed and discussed. In the last parts of the paper the conclusion are presented.
Współcześnie jedną z metod poprawy efektywności pracy silników lotniczych jest obniżanie jednostkowego zużycia paliwa, przy jednoczesnym niezmienianiu jego ciągu. Umożliwia to m.in. doskonalenie procesów wewnętrznych w silniku. Obecna technologia wytwarzania oraz komputerowe wsparcie procesów projektowania pozwala produkować zespoły silnika o coraz wyższej efektywności procesów wewnętrznych. Żeby optymalnie organizować proces podnoszenia efektywności pracy silnika wymagana jest znajomość wpływu modyfikacji efektywności poszczególnych zespołów na parametry użytkowe silnika. Umożliwia to oszacowanie kosztów i ocenę efektywności proponowanych modyfikacji silnika. W pracy przeprowadzono analizę wrażliwości modelu silnika dwuprzepływowego na zmianę efektywności procesów przepływowo-cieplnych w zespołach silnika. Efektywność procesów w zespołach silnika opisano poprzez wskaźniki strat ciśnienia oraz sprawności, zaś badanymi parametrami pracy silnika były ciąg jednostkowy i jednostkowe zużycie paliwa. Na początek scharakteryzowano dwa zasadnicze typy silników dwuprzepływowych - z mieszalnikiem i bez. Następnie przedstawiono przyjęty model silnika oraz wskaźniki oceny procesów wewnętrznych w zespołach i metodykę badań. W kolejnym kroku przeprowadzono badania z wykorzystaniem metod bazujących na metodzie małych odchyleń. Wyniki badań przedstawiono w postaci graficznej i omówiono porównując obydwie analizowane konstrukcje. Na koniec zaprezentowano wnioski do pracy.
Źródło:: Journal of KONES; 2008, 15, 3; 201-207
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 42.

Tytuł:: Investigation of the turbofan with mixer engine model sensitivity of thermal-flow process modification in the engines components
Badania wrażliwości modelu silnika dwuprzepływowego z mieszalnikiem strumieni na zmianę efektywności procesów przepływowo-cieplnych w zespołach silnika
Autorzy:: Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/244315.pdf
Data publikacji:: 2007
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: silniki lotnicze
silniki odrzutowe
modelowanie silników odrzutowych
charakterystyki silnika odrzutowego
aircraft engines
turbojet engines
modelling of turbojet engines
turbojet engine characteristics
Opis:: The turbofan with mixer engine model sensitivity of the thermal-flow processes effectiveness in the engine components changes was analyzed. The model of turbofan engine with the mixed exhaust stream is so complicated to use the small deviation methods to solve this problem. On that reason the own author methods to analyze this problem was proposed. During investigation it was revealed that the changes of some processes effectiveness leads to change of pressure inflow to the mixer and this cause to change of mixer process effectiveness. The mixer pressure drop coefficient decries so slightly but it should be taking into consideration during exact calculations. In the main parts of paper the results of simulation of engine work parameters sensitivity of the thermal-flow processes effectiveness changes is presented and discussed. The specific thrust and specific fuel consumption were chosen as the engine work parameters. The model responds for change of internal process effectiveness in all range and for small step was analyzed. The conclusions are presented in final parts of the paper. The essential influence on relations between the change of the efficiency of rotor sets and with specific parameters has compression rate of compressor. Generally the improvement performers of the excellence processes give better effects at the lower temperature value in front of the turbine.
Źródło:: Journal of KONES; 2007, 14, 4; 119-126
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 43.

Tytuł:: Rotating detonation engine simulations in-house code - REFloPS
Symulacje silnika z wirujacą detonacją (RDE) w kodzie REFloPS
Autorzy:: Folusiak, M.
Kobiera, A.
Wolański, P.
Powiązania:: https://bibliotekanauki.pl/articles/213102.pdf
Data publikacji:: 2010
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: siniki i paliwa lotnicze
aerodynamika i mechanika lotu
materiałoznawstwo
aircraft engines and fuels
aerodynamics and mechanics of flight
materials science
Opis:: The paper presents the results of three-dimensional preliminary simulations of a detonation propagating in Rotating Detonation Engine chamber. Simulations were performed using in-house code REFloPS (Reactive Euler Flow Solver for Propulsion Systems)[1]. The description of the code and presented results are also included in MSc thesis of Folusiak and Swiderski [2].
W artykule przedstawiono wyniki trójwymiarowych symulacji detonacji w komorze silnika z wirującą detonacją (RDE). Symulacje przeprowadzono przy użyciu kodu REFloPS, który jest wynikiem pracy magisterskiej dwóch pracowników Instytutu Lotnictwa.
Źródło:: Prace Instytutu Lotnictwa; 2010, 5 (207); 3-23
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 44.

Tytuł:: Impact of the additives used in mineral jet fuels on the lubricating properties of synthetic fuels for turbine aircraft engines
Autorzy:: Dzięgielewski, W.
Kaźmierczak, U.
Kulczycki, A.
Ozimina, D.
Powiązania:: https://bibliotekanauki.pl/articles/245539.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: lubricity
fuels for turbine aircraft engines
synthetic components
additives
Opis:: Hydrocarbon containing synthetic fuels represent a promising alternative fuels. Despite different chemical compositions, their properties should be similar to properties of mineral fuels, as they are designed for the same drive units. The basic parameter related to the protection of the adequate service life of the power supply devices, including precision pairs, is lubricity. Lubricity depends on a number of factors, including these related to the chemical composition of fuel components and operating additives introduced into fuels in order to modify their properties. The preliminary results of research on the effect of additives: lubricating, anti-corrosion and anti-electrostatic once, on the lubricating properties of a synthetic fuel are shown in the paper. It was observed that there are relations between the content of additives and the dynamics of film formation. It is significant that this does not apply only to the lubricating additive, but also the additive, which protects the correct electrostatic balance by providing sufficiently high electrical conductivity of the fuel. This may indicate that the formation of a lubricating film remains in relation to the intensity of energy transport from the lubricated surface to the molecules of lubricating additives inside the film. The results shown in the paper preliminary confirm the hypothesis, that synthetic components of fuels change the concentration of ordered molecular structures (which are present in mineral part of fuels and which can be responsible for energy transport inside the lubricating film), what resulted in worse fuel ability to create protective film, and anti-electrostatic additive improves lubricity of blends of synthetic and mineral components.
Źródło:: Journal of KONES; 2018, 25, 2; 121-128
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 45.

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

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