Temat: aero engine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Early detection of fatigue cracks in turbine aero - engine rotor blades during flight
Autorzy:: Szczepanik, R.
Powiązania:: https://bibliotekanauki.pl/articles/245961.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aero-engines
diagnostic of aircraft engine
non-contact blade-vibration measurement
damage to the aircraft
Opis:: The author shows results of research done in the Air Force Institute of Technology concerning design, development and implementation of modern diagnostic systems for aero-engines. The papers gives brief description of a project of a new advanced monitoring system basing on non-contact blade-vibration measurement. Recent monitoring systems for engines offer a great potential to reduce the high maintenance costs of aircraft while increasing reliability and safety. These systems check for abnormal engine responses to detect failures, saving lives and reducing secondary damage to the aircraft. A phenomenon of dynamic change of an aero-engine compressor blades natural frequency in course of fatigue cracks propagation in their roots on the example of a Polish turbojet engine is described. On the ground of this phenomenon main working principles of a device, which measures vibrations of turbine engine rotor blades with application of the noninterfering discrete method (MDPh), used for early detection of first stage compressor blade cracks are discussed. Typical representation of the first stage compressor blades vibration during engine acceleration, representation of the first stage blades vibration during engine acceleration and deceleration with steady-state stator distortions, crack initiation and propagation symptoms in blades, comparison of blade vibration spectra of the same blades for different conditions are presented in the paper.
Źródło:: Journal of KONES; 2013, 20, 1; 337-342
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Silnik lotniczy jako obiekt badań tribologicznych
Aero-engine as the object of tribological research
Autorzy:: Nidzgorska, Adrianna
Witoś, Mirosław
Perczyński, Jerzy
Kułaszka, Artur
Powiązania:: https://bibliotekanauki.pl/articles/38933889.pdf
Data publikacji:: 2023
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: lotnictwo
tarcie
diagnostyka
badanie tribologiczne
silnik lotniczy
instalacja olejowa
aviation
friction
diagnostics
tribological testing
aero-engine
oil system
Opis:: Podczas pracy silników lotniczych (turbinowych i tłokowych) występują procesy zużycia w węzłach tribologicznych, które w znaczny sposób wpływają na niezawodność i bezpieczeństwo eksploatacji statków powietrznych. W artykule przedstawiono aspekty diagnostyki tribologicznej silników lotniczych bazującej na okresowych badaniach próbek środka smarnego w laboratoriach. Na początku przedstawiono obiekt badań z uwzględnieniem cech konstrukcyjnych, parametrów pracy i stosowanych środków smarnych oraz podstawy teoretyczne badań tribologicznych. Następnie opisano metody badań stosowane w diagnostyce tribologicznej silników lotniczych, uwzględniając procesy starzenia i zanieczyszczenia środków smarnych, normy, metodyki badawcze i doświadczenia eksploatacyjne opisane w literaturze, w tym krzywą podatności eksploatacyjnej. Możliwości metod badawczych zobrazowano wynikami z okresowych badań tribologicznych silników turbinowych, uzyskanymi w akredytowanym laboratorium diagnostyki systemów tribologicznych. W dalszej części wskazano rolę analizy trendu i kryteriów statystycznych w procesie diagnozowania i zarządzania ryzykiem eksploatacji silników lotniczych, eksploatowanych zarówno według stanu technicznego, jak i planowanych obsług technicznych (resursów). Zasygnalizowano możliwość poprawy wiarygodności diagnostyki tribologicznej silników lotniczych na bazie doświadczeń z przemysłu – monitorowania wybranych parametrów tribologicznych w czasie rzeczywistym. W podsumowaniu wskazano na wysoką efektywność i rolę diagnostyki tribologicznej w utrzymaniu bezpieczeństwa eksploatacji floty różnych typów statków powietrznych.
During the operation of aero-engines (turbine and piston engines), wear processes occur in tribological nodes, which significantly affect the reliability and safety of flight operations. This paper presents aspects of tribological diagnostics of aircraft engines based on periodic testing of lubricant samples in laboratories. Firstly, the object of research with its design features, operating parameters and used lubricants is presented, as well as the theoretical basis of tribological testing. This was followed by a description of the testing methods used in tribological diagnostics of aero-engines, taking into account lubricant degradation and contamination processes, standards, testing methodologies and operating experience described in the literature, including the machine failure curve. Next, the capabilities of the testing methods are illustrated with results from periodic tribological testing of turbine engines, obtained at an accredited tribological systems diagnostics laboratory. In the following section, the role of trend analysis and statistical criteria in the process of diagnosing and managing the risk of operation of aero-engines, exploited according to both their technical condition and planned maintenance, was indicated. Then, the possibility of improving the reliability of tribological diagnostics of aero-engines on the basis of experience from industry - real-time monitoring of selected tribological parameters - was signalled. In conclusion, the high efficiency and role of tribological diagnostics in maintaining the operational safety of a fleet of different aircraft types is indicated.
Źródło:: Journal of KONBiN; 2023, 53, 3; 87-128
1895-8281
2083-4608
Pojawia się w:: Journal of KONBiN
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: A Novel Approach for the Assembly of Fabricated Aero-Engine Components
Autorzy:: Jayaweera, N.
Webb, P.
Johnson, C.
Powiązania:: https://bibliotekanauki.pl/articles/971261.pdf
Data publikacji:: 2009
Wydawca:: Wrocławska Rada Federacji Stowarzyszeń Naukowo-Technicznych
Tematy:: robotic assembly
best-fit algorithm
aero-engine components
Opis:: Currently the manufacturing of aero-engine intercase is primarily a single piece titanium casting and has slightly deteriorated material properties as compared to sheet metal parts and has long manufacturing lead time. As an alternative solution to above problems, the VITAL (Environmentally Friendly Aero Engines) project aims to design, manufacture and test the critical technologies required to develop new type of clean and low noise aero engines by developing innovative technical solutions to reduce the engine's weight, thereby reducing both fuel consumption and CO2 emission. This requires the fabrication of small and weight optimised parts which will be automatically manipulated, welded, assembled and inspected in a flexible fabrication cell. The paper introduces a novel techniques for compensating the deformation that occur in aero-engine fabricated components and potential component handling errors using standard industrial robots, an advanced end-effector, mathematical processing, non-contact metrology systems and cell control system. The system described in this paper uses in-process measurement sensors to determine the component's exact location prior to the assembly operation. The core of the system is a set of algorithms capable of best fitting measurement data to find optimal assembly of components.
Źródło:: Journal of Machine Engineering; 2009, 9, 4; 61-70
1895-7595
2391-8071
Pojawia się w:: Journal of Machine Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Robotic assembly of aero-engine components
Autorzy:: Jayaweera, N.
Webb, P.
Ye, C.
Johnson, C.
Powiązania:: https://bibliotekanauki.pl/articles/1429288.pdf
Data publikacji:: 2008
Wydawca:: Wrocławska Rada Federacji Stowarzyszeń Naukowo-Technicznych
Tematy:: robotic assembly
aero-engine components
Opis:: The VITAL (EnVIronmenTALly Friendly Aero Engines) project funded by the European Commission under Framework 6 aims to provide significant reductions in aero-engine fuel burn, noise and emissions through the development of innovative design and manufacturing techniques. One method of reducing the amount of fuel burnt, and hence CO2 produced, is to reduce the weight of the engine. A significant proportion of an engine's weight is due to the large castings used to form the main non-rotating structures; the replacement of these with fabricated structures could provide a significant weight reduction. This paper describes the design and implementation of a robotic assembly cell for complex aero-engine components. A series of experiments were performed to prove the feasibility of the automated assembly process. The results presented indicate that automated robotic assembly is feasible and cost effective.
Źródło:: Journal of Machine Engineering; 2008, 8, 3; 5-16
1895-7595
2391-8071
Pojawia się w:: Journal of Machine Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Study of bypass ratio increasing possibility for turbofan engine and turbofan with inter turbine burner
Autorzy:: Jakubowski, Robert
Powiązania:: https://bibliotekanauki.pl/articles/244907.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aero engine
turbofan engine
combustion engines
aero engine development
turbine inter stage burner
Opis:: Current trends in the high bypass ratio turbofan engines development are discussed in the beginning of the paper. Based on this, the state of the art in the contemporary turbofan engines is presented and their change in the last decade is briefly summarized. The main scope of the work is the bypass ratio growth analysis. It is discussed for classical turbofan engine scheme. The next step is presentation of reach this goal by application of an additional combustor located between high and low pressure turbines. The numerical model for fast analysis of bypass ratio grows for both engine kinds are presented. Based on it, the numerical simulation of bypass engine increasing is studied. The assumption to carry out this study is a common core engine. For classical turbofan engine bypass ratio grow is compensated by fan pressure ratio reduction. For inter turbine burner turbofan, bypass grown is compensated by additional energy input into the additional combustor. Presented results are plotted and discussed. The main conclusion is drawing that energy input in to the turbofan aero engine should grow when bypass ratio is growing otherwise the energy should be saved by other engine elements (here fan pressure ratio is decreasing). Presented solution of additional energy input in inter turbine burner allow to eliminate this problem. In studied aspect, this solution not allows to improve engine performance. Specific thrust of such engine grows with bypass ratio rise – this is positive, but specific fuel consumption rise too. Classical turbofan reaches lower specific thrust for higher bypass ratio but its specific fuel consumption is lower too. Specific fuel consumption decreasing is one of the goal set for future aero-engines improvements.
Źródło:: Journal of KONES; 2019, 26, 2; 61-68
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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