Temat: aircraft engines - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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: 2.

Tytuł:: Actual needs and Possibilities to producing Bio-Jet
Autorzy:: Naumienko, B.
Rarata, G.
Powiązania:: https://bibliotekanauki.pl/articles/213104.pdf
Data publikacji:: 2010
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: silniki i paliwa lotnicze
aerodynamika i mechanika lotu
materiałoznawstwo
paliwo typu Bio-Jet
aircraft engines and fuels
aerodynamics and mechanics of flight
materials science
Bio-Jet fuel
Opis:: Since the beginning of the century, various studies, reports and popular scientific papers have investigated the potential for use of biofuels in aviation. In its recent actions EU also perceives the need for he introduction of sustainable biofuels to help reduce dependence on fossil fuels in air transport and reduce GHG emissions by the air industry. Thus, various feedstocks and conversion technologies for production of biofuels for aviation are currently being investigated within EU (SWAFEA, ALFA-BIRD and Clean Sky JTI). The current EU policy states that sustainable bio-jet fuels are the only option that can be delivered over the medium term, in time to make a significant contribution to EU 2050 emission reduction targets [11]. However, it seems that commercial producers of fuels cannot justify investment in a Bio-Jet fuel production facility until guaranteed availability of sustainable feedstock and clear legislation. EU government is currently taking necessary steps to open a long-term option for the aviation biofuel production in the local market and to support its development. Whereas microalgae is certainly a feedstock considered by many future Bio-Jet producers. Only microalgae seems to offer vast potential as a source of aviation biofuels, however on the more distant horizons of an industry, in which long-term time scales are certainty. Besides, microalgae co-products are utilised at making complex organic compounds like B and C vitamins and beta-carotene that are used as fragrances, flavourings, pigments and supplements. Generally, the research done so far have demonstrated that only a portion of the crude algal oil is suitable for making biodiesel fuel, and most of it can be used to produce gasoline and Bio-Jet like fuels.
W artykule przedstawiono skrót aktualnych osiągnięć technologicznych na temat potencjalnego zastosowania biopaliw w lotnictwie. Zaznaczono również, że ostanie dyrektywy Komisji Europejskiej także faworyzują wprowadzanie biopaliw do transportu lotniczego, celem zmniejszania zależności od importowanych paliw ropopochodnych oraz obniżania emisji gazów cieplarnianych. Wymieniono różne podejścia technologiczne do zagadnienia produkcji biopaliw dla lotnictwa. Autorzy identyfikują mikroalgi jako najlepszą alternatywę do produkcji biopaliwa lotniczego w dłuższej perspektywie. Podobnie wielu innych producentów biopaliw rozważa taki scenariusz. Biomasa z mikroalg bowiem wydaje się być najbardziej obiecującym źródłem do produkcji bio-zamiennika paliwa Jet A-1, jak również wielu innych, użytecznych związków organicznych. Ponadto, jak wynika z dotychczas prezentowanych badań, jedynie część biomasy z mikroalg jest użyteczna dla produkcji paliwa typu biodiesel, znacznie więcej zaś może zostać wykorzystane do produkcji benzyn oraz paliwa typu Bio-Jet.
Źródło:: Prace Instytutu Lotnictwa; 2010, 5 (207); 24-31
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

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

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Skocz do pozycji: 4.

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: 5.

Tytuł:: Analysis of applicability of thermography to assess health of gas turbine blades
Autorzy:: Kułaszka, A.
Błachnio, J.
Powiązania:: https://bibliotekanauki.pl/articles/246976.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: engines
aircraft engineering
mechanical engineering
Opis:: A gas turbine is one of the most heavily loaded, both mechanically and thermally, structural components of an aircraft turbine engine. Hence, the most common reasons for failure are overheating and thermal fatigue of the blade material. It is of great significance for the safety of aeronautical systems that service is monitored; this is carried out to verify the health of these items using all available diagnostic methods. The primary aim is to detect and identify, as early as possible, any probable hazards to the engine. The preliminary assessment of the gas turbine blades condition is carried out via a visual inspection e.g. using a video borescope. During any repair, the preliminary assessment is conducted with a visual method, which is followed with some other non-destructive inspection techniques, e.g. flaw detection, intended to provide full colour images. The essential assessment of the blade condition consists in metallographic examination which precludes further operational use of the item. Probable errors in this assessment usually result in considerable cost of unnecessary repairs of the entire engine. Presented in the paper is the pulse thermography technique being a new NDT method, which is capable of diagnosing changes in the blade condition and to detect early stages of damages to turbine blades. Results of inspections of the blades subjected to high temperature and corresponding changes in signals of thermal response of the blade material stimulated with a heat pulse have also been given. Effects of the testing work have been used to detect changes, against temperature, in thermophysical properties of super alloy used in gas turbine blades. The results have been successfully verified using metallographic examination. To conclude: the thermographic method provides good reliability of the assessment of changes in the microstructure of the blade.
Źródło:: Journal of KONES; 2013, 20, 2; 237-244
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

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: 7.

Tytuł:: Analysis of dimensional accuracy of blade of aircraft engine using a coordinate measuring machine
Autorzy:: Budzik, G
Kubiak, Krzysztof
Zaborniak, M.
Przeszłowski, Ł.
Dziubek, T.
Cygan, M.
Tutak, M.
Matysiak, H
Powiązania:: https://bibliotekanauki.pl/articles/244267.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines turbine blades
optical measurements
coordinate measuring technique
Opis:: Technological process of aircraft engine turbine blades requires control of blade geometric parameters. Innovation technologies for measurement of aircraft engine turbine blades are based on coordinate numerical machines – measurement process is based on processing of numerical data obtained by measurement using coordinate measuring machines. The paper presents the opportunity of analysis of dimensional accuracy of aircraft engine turbine blades measurements using coordinate measuring machine (CMM). Coordinate measuring machine allows specifying full methodology for designation of complex dimensions of physical objects (blade of aircraft engine) and transforming them into a computer program space of coordinate measuring devices. Presented paper includes capabilities of device used in the study to improve the measurement process and blades geometry analysis in the technological and economical aspects. Another issue described in the paper is impact of measurement performance in automatic mode on the quality of performance – the numerical model of geometry, from the standpoint of accuracy and number of collected data points in time. Measurements using a coordinate measuring machine are among the most accurate methods of measuring. The paper includes an analysis of conditions related to the measurement works, such as the process of preparing the model, measurement equipment and data processing capacity. As the result, methodology of (CMM) measurements of aircraft engine turbine blades will be presented.
Źródło:: Journal of KONES; 2014, 21, 2; 33-37
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Analysis of the application of distributed propulsion to the AOS H2 motor glider
Autorzy:: Kuźniar, Michał
Orkisz, Marek
Powiązania:: https://bibliotekanauki.pl/articles/244774.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engineering
engines
mechanical engineering
Opis:: The paper describes the selection of a distributed propulsion for the AOS H2 motor glider (selection of engines, their number, and propellers) and determination of its performance. This analysis is related to the research conducted on environment friendly and hybrid propulsions in various research centres. The main aim of the analyses conducted is to increase the performance of vehicles powered by electric motors. The batteries have a low density of energy, i.e. the ratio of mass to cumulated energy. Instead of a battery set, it is possible to apply a hybrid- electric system, where the combustion engine works as a generator or an electric-hydrogen generator, where the hydrogen cell supports a small set of batteries. One of such flying vehicles, fitting in this trend, is the AOS H2 motor glider built at the Rzeszow University of Technology in cooperation with other universities. It is a hybrid aircraft, equipped with a hydrogen cell, which together with a set of batteries is a source of electricity for the Emrax 268 electric motor. To increase the vehicle's performance (the range and flight duration), it is possible to use a distributed propulsion. This type of propulsion consists in placing many electric motors along the wingspan of the aircraft. Appropriate design of such a system (propeller diameters, engine power, number of engines) can improve the aerodynamic and performance parameters of the airframe. An analysis of the performance for the selected flight trajectory for this propulsion variant was conducted and compared to the performance of the AOS H2 motor glider equipped with traditional propulsion. The consumption of hydrogen was also determined for both systems. The results obtained were presented in the diagrams and discussed in the conclusions.
Źródło:: Journal of KONES; 2019, 26, 2; 85-92
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

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: 10.

Tytuł:: Application of a panel method with viscous-in-viscid interaction for the determination of aerodynamic characteristics of Cesar Base-Line aircraft
Autorzy:: Stalewski, W.
Sznajder, J.
Powiązania:: https://bibliotekanauki.pl/articles/213118.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 article presents details of implementation of of a panel method with viscous-inviscid interaction in an in-house developed code Coda3d. The code was applied for the determination of aerodynamic characteristics of baseline aircraft in a European Union 6-th Framework Program Cesar, aimed at acceleration of design and introduction to the market of light aircraft. The implemented physical model assumes that the flowfield around a flying object is divided into two zones. In the outer zone the flow is assumed inviscid, irrotational, compressible and may be modeled by Prandtl-Glauert equation. In the vicinity of the surface, up to the conventional border of the boundary layer the flow is modeled by a system of ordinary differential equations, which are derived from Prandtl boundary layer equations through integration in the direction normal to the surface. The system of boundary layer integral equations is then integrated in the direction of flow, separately on upper and lower surface of wing, starting from the stagnation point. The process of aligning of flow velocities on the outer border of boundary layer derived from viscous and inviscid models is conducted iteratively. The results of flow analysis include distribution of tangential velocities, pressure, friction drag coefficient and position of flow separation. Because of low computational cost and capabilities of estimation of viscous drag and and aerodynamic characteristics at high angles of attack, the presented method is especially suitable for design and optimistation process conducted in small enterprises.
Artykuł prezentuje szczegóły implementacji metody panelowej ze sprzężeniem lepko-nielepkim w kodzie obliczeniowym Coda3d oraz jego zastosowanie do wyznaczenia charakterystyk aerodynamicznych samolotu „baseline” w VI Programie Ramowym UE Cesar, mającym na celu przyśpieszenie projektowania oraz wprowadzania na rynek lekkich samolotów. Zaimplementowany model opływu dzieli przestrzeń obliczeniową na dwie strefy. W strefie zewnętrznej przepływ jest nielepki, nierotacyjny, ściśliwy imoże być modelowany przez równanie Prandtla-Glauerta. Przepływ w sąsiedztwie powierzchni, aż do umownej granicy warstwy przyściennej modelowany jest przy pomocy równań całkowych warstwy przyściennej otrzymanych z równań Prandtla warstwy przyściennej przez ich scałkowanie w kierunku normalnym do powierzchni. Równania całkowe warstwy przyściennej są następnie całkowane w kierunku przepływu, oddzielnie na górnej i dolnej powierzchni skrzydła, zaczynając od punktu spiętrzenia. Uzgadnianie prędkości przepływu na granicy warstwy przyściennej prowadzone jest w procesie iteracyjnym. Wyniki analizy przepływu obejmują rozkład prędkości stycznych do powierzchni, ciśnienia, współczynnik oporu tarcia oraz położenie punktu oderwania przepływu. Przedstawiona metoda wyznaczania charakterystyk aerodynamicznych jest szczególnie przydatna w procesie projektowania i optymalizacji prowadzonym w małych przedsiębiorstwach z powodu jej niskich kosztów obliczeniowych oraz możliwości wyznaczania oporu lepkiego oraz charakterystyk na dużych kątach natarcia.
Źródło:: Prace Instytutu Lotnictwa; 2010, 5 (207); 76-97
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

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: 12.

Tytuł:: Bilans energetyczny wirników dwuprzepływowych silników odrzutowych
The rotors energy balance in turbofan jet engines
Autorzy:: Balicki, W.
Głowacki, P.
Szczeciński, S.
Kozakiewicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/212277.pdf
Data publikacji:: 2016
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: napędy lotnicze
turbinowe silniki odrzutowe
sprężarki osiowe
bilans energii
aircraft power plants
turbine jet engines
axial compressors
energy balance
Opis:: W artykule przybliżono problematykę bilansowania procesów energetycznych turbinowych silników odrzutowych pracujących w lotniczych zespołach napędowych dla potrzeb analizy i oceny podstawowych parametrów pracy. Przedstawiono - rzadko podejmowany w literaturze specjalistycznej w i programach nauczania - problem ogromnych energii niezbędnych do napędu wentylatorów i sprężarek największych współczesnych dwuprzepływowych turbinowych silników odrzutowych wykorzystywanych powszechnie w lotnictwie dalekiego zasięgu. Na podstawie prostego modelu obliczeniowego oceniono wartości przenoszonych mocy oraz wpływ parametrów przepływowych i cech konstrukcyjnych silników na ich osiągi i sprawność efektywną. Moce potrzebne do napędu wentylatorów najwiekszych obecnie używanych silników sięgają 70 MW, a momenty przenoszone przez wary łaczące turbiny z wentylatorami mogą - w warunkach startowych - sięgać 70 000 Nm.
The article presents problems of energy balancing processes in the turbine jet engines that work in aircraft propulsion units and its influence on analysis and evaluation of basic operating parameters. The paper describes the problem - which is rarely discussed in the specialist literature and in school curricula - of huge amounts of energy required to drive the fan and compressor of huge modern turbofan jet engines which are widely used in long-range aviation. On the basis of a simple calculation model, the value of transmitted power as well as the influence of flow parameters and the design characteristics of engines on their performance and efficiency have been estimated. Powers needed for propulsion of the fans at the biggest engines that are currently in use are up to 70 MW, while torques on shafts connecting turbines with fans can reach up to 70,000 Nm at take-off conditions.
Źródło:: Prace Instytutu Lotnictwa; 2016, 3 (244); 321-328
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Checking the Correctness of the Process of Brazing of the Honeycomb Seal to the Base by Ultrasonic Method
Autorzy:: Świerek, Agata
Krysztofik, Józef
Matczak, Wojciech
Niepokólczycki, Antoni
Powiązania:: https://bibliotekanauki.pl/articles/24201175.pdf
Data publikacji:: 2022
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: turbine aircraft engines
honeycomb seals
hard soldering
non-destructive testing
soldering correctness control
Opis:: This work is focused on the checking of the correctness of the brazing process of honeycomb seals to stationary elements of aircraft turbine engines. It describes this process, paying attention to the aspects that have a fundamental impact on whether the seal will be brazed to the base as required, or whether unacceptable areas of non-brazing will appear. The aim of the study was to check the possibility of using the ultrasonic method to check the correctness of the brazing process of honeycomb seals and to compare the tests carried out using this method with the mostly used visual tests. The research carried out as part of the work showed very well that there are reasons to use the ultrasonic defectoscopy method to test the correctness of the brazing process of honeycomb seals in the elements of aircraft engines. This method also makes it possible to automate the checking process, fully document it and objectively assess the correctness of the connection. The results obtained in the study provide a very good starting point for further research, the aim of which will be to implement the ultrasonic defectoscopy method for testing the correctness of brazing honeycomb seals into practice in industrial conditions.
Źródło:: Fatigue of Aircraft Structures; 2022, 14; 47--68
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Combustor liner cooling methods - numerical simulation
Autorzy:: Lazarczyk, M.
Domański, R.
Powiązania:: https://bibliotekanauki.pl/articles/247755.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:: The objective of this thesis is to compare various methods of combustor wall cooling and to evaluate advantages and disadvantages of each applied cooling methods. It was determined that the flrst task was to verify how much air is coming through singe radial hole with 2.5% pressure drop between hot and cold part ofcombustion chamber. Flowcheck was calculated also to see how geometry of cooling hole affects hole effective area. Second task was to generale 3d model and mesh of both calculated types of cooling. Each model mesh was covered with boundary layer in order to better simulate conditions near the combustion chamber walls and obtain accurate results. In order to run back-to-back analysis, all created models have the same number of mesh elements, same materials used, samefluent settings, same operating and boundary conditions. Geometry of all models described above was created using Unigraphics NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre-processor GAMBITŽ. The airflow and conjugated heat transfer analysis was calculated in program FLUENTŽ. The goal of this thesis was to obtain temperature fields and distribution in the combustion chamber domain (lip and panel wall) and to evaluate if applied cooling is sufficient to cool down heat loaded part of the combustor chamber.
Źródło:: Journal of KONES; 2010, 17, 4; 277-286
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Comparing methods of calculating aircraft engine emissions of harmful exhaust components during the takeoff and landing cycle in the airspace of an airport
Autorzy:: Głowacki, Paweł
Kalina, Piotr
Kawalec, Michał
Powiązania:: https://bibliotekanauki.pl/articles/36455315.pdf
Data publikacji:: 2022
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: harmful emissions
exhaust gases
aircraft engines
LTO cycle
Opis:: An airport authority needs accurate information about the actual amount of harmful emissions being generated within its airspace, to be able to take measures leading to their reduction. This article presents two methods for estimating the amount of these emissions from aircraft engines during the take off and landing cycle (LTO) in the airspace of a medium-sized airport: one based on the total amount of the aircraft annually operated in it, and a second, more precise, one for a specific airline annually operating at this airport. The conclusions stemming from the comparison of these methods can support the introduction of operational and technical procedures reducing harmful emissions in the airport airspace during LTO cycle.
Źródło:: Transactions on Aerospace Research; 2022, 2 (267); 62-68
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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