Wszystkie pola: Aircraft Fatigue - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Numerical Simulation of Fatigue Fracture of the Turbine Disc
Autorzy:: Witek, L.
Powiązania:: https://bibliotekanauki.pl/articles/97889.pdf
Data publikacji:: 2012
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: aircraft engine
crack propagation analysis
finite element method
fatigue fracture
Opis:: This paper presents the results of the crack propagation analysis of an aircraft engine turbine disc. In the first part of the work the finite element method was used for calculation of the stress state and the stress intensity factor (SIF, K_I, K-factor) in the turbine disc with an embedded quarter-elliptical corner crack, subjected to low-cycle thermo-mechanical fatigue. To refine the K-factor calculation, specially degenerated finite elements were used. These elements provide stress singularity suitable for the linear-elastic material of the disc. The performed calculations yielded the stress intensity factor K_I for different crack sizes. Subsequently, ΔK parameter was determined as a difference of the K_I values calculated for the turbine’s speeds equal to 6373 and 14200 RPM. Based on the Paris-Erdogan equation and the obtained ΔK values, the fatigue crack growth plot for the turbine disc subjected to complex thermo-mechanical loads was determined.
Źródło:: Fatigue of Aircraft Structures; 2012, 4; 114-122
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Methods of counting aircraft turbine engines operating cycles
Metody zaliczania cykli pracy lotniczych silników turbinowych
Autorzy:: Chachurski, R.
Głowacki, P.
Szczeciński, S.
Powiązania:: https://bibliotekanauki.pl/articles/212469.pdf
Data publikacji:: 2011
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: zmęczenie silników turbinowych
zaliczanie cykli pracy silników lotniczych
lotnicze silniki turbinowe
turbine engine fatigue
aircraft engine
turbine engine
low-cycle fatigue
cycles number
Opis:: The issue of low-cycle fatigue is very important in terms of operational safety of aircraft turbine engines. This paper discusses methods, which are used in US aviation industry to determine boundary cycle counts, as well as methods of counting turbine engine operating cycles allowing to determine the residual safe operation time (hard time), expressed in cycles. Methods are discussed, which are used for both older types of engines as well as for present-day ones. In the paper titled „Zmęczenie niskocyklowe konstrukcji i jego minimalizacja” (Low-cycle structural fatigue and its minimization), published in volume no. 199/2009 of Prace Instytutu Lotnictwa (Proceedings of the Institute of Aviation) contains a schematic presentation of loads acting on components in the „hot section” of an aircraft turbine engine, as well as loads’ operational dependencies on engines’ operating conditions and operating ranges affecting their lowcycle structural fatigue. The paper pointed out that findings related to this type of loads had caused engine safe operation times to be expressed both in hours as well as in cycles. Methods for determining the number of cycles „utilized” by main engine modules and their important parts affecting operational safety, as well as maximum limits of operational cycle which if exceeded should require replacement of respective modules or individual parts had been imposed on operators by engine manufacturers. They are initially determined basing on fatigue tests performed on standard specimens of structural material and then based on fatigue tests of production parts and tests of complete engines. This paper is a further development of these previously discussed topics.
Zagadnienie zmęczenia niskocyklowego jest bardzo istotne z punktu widzenia bezpieczeństwa eksploatacji lotniczych silników turbinowych. W artykule przedstawiono sposoby wyznaczania granicznej liczby cykli stosowane w lotnictwie USA, a także metody zliczania cykli pracy silnika turbinowego w celu określenia pozostałości czasu jego bezpiecznej eksploatacji (resursu) wyrażonego w cyklach. Opisano metody wykorzystywane podczas użytkowania zarówno silników starszych typów, jak i współczesnych.
Źródło:: Prace Instytutu Lotnictwa; 2011, 8 (217); 5-13
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: The study on algorithm for identification the fatigue crack length of compressor blade based on amplitude-frequency resonant characteristics
Autorzy:: Lichoń, D.
Bednarz, A.
Powiązania:: https://bibliotekanauki.pl/articles/243684.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: fatigue failure
crack length
compressor blade
aircraft engine
failure identification algorithm
Opis:: The article is focused on building the algorithm for identification the fatigue crack length in the first stage of compressor blade of the helicopter PZL-10W turbo-shaft engine. The fatigue wear of compressor blade is a process in which the fatigue crack begins at the structural notch of the working part. For compressor blade, the crack starts at the leading edge and progress along the blade chord. Due to working conditions, the compressor blades are referred to as critical components. The helicopter rotor downwash can easily lift particles form the ground that may cause damages in the compressor section. Aircraft engines are designed so that the rotational speed of impeller remains below the resonant frequency. However, the pulsation of working medium or mechanical vibrations may cause temporary increase of vibration frequency. The appearance of structural notch combined with temporary increase of vibrations may initiate the fatigue failure. The works undertaken at the Department of Aircraft and Aircraft Engines, Rzeszow University of Technology provided a wide spectrum of research data of amplitude-frequency (A-F) characteristics of 1st stage of compressor blade. For different crack lengths, the fatigue tests of resonant frequency and asymmetry of A-F characteristics were acquired. The crack lengths were measured by fluorescent or infrared mapping method. The aim of the article is to develop the numerical method for identification of crack length of compressor blade basing on A-F characteristics. The studies on A-F characteristics in order to find correlations between crack length, resonant frequency and characteristics asymmetry were performed. The next step was to build the algorithm for identification the crack length when only A-F characteristic is known. The article contains the description of researches background, A-F characteristics unique features, algorithm detailed methods of work and sample use of algorithm in identification the crack length.
Źródło:: Journal of KONES; 2017, 24, 4; 157-164
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Influence of the cyclic hardening model on the results of the numerical analysis of fatigue life on example of the compressor blade
Autorzy:: Bednarz, Arkadiusz
Powiązania:: https://bibliotekanauki.pl/articles/245046.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: fatigue life
compressor blade
aircraft engine
cyclic hardening
numerical analysis
Opis:: The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.
Źródło:: Journal of KONES; 2019, 26, 2; 7-14
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Aspekty metrologiczne bezdotykowego diagnozowania wirujących łopatek sprężarki
Metrological aspects of non-contact roating blade measurements
Autorzy:: Witoś, M.
Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/209146.pdf
Data publikacji:: 2008
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: odstęp czasu
nierównomierne próbkowanie
łopatki
zmęczenie
silniki lotnicze
diagnostyka silników lotniczych
tip timing
nonuniform sampling
blades
fatigue
aircraft engine
diagnosis of aircraft engine
Opis:: Przedstawiono podstawy teoretyczne stosowania elastycznego znacznika fazy - wirującej i drgającej łopatki sprężarki - do kompleksowego diagnozowania turbinowego silnika lotniczego (metoda tip timing). Wskazano na rolę numerycznych metod analizy w rozdzieleniu składowych sygnału pomiarowego (aperiodycznej i oscylacyjnej) oraz potrzebę weryfikacji istniejących algorytmów analizy danych, pochodzących z nierównomiernego próbkowania. Omówiono 15-letnie spostrzeżenia eksploatacyjne stosowania metody na samolotach TS-11 "Iskra".
The paper presents theoretical background of using elastic key phasor-rotating and vibrating compressor blade - for complex jet engine diagnosis (tip timing method). The role of numerical methods of measurement signal decomposition onto parts (aperiodic and oscillation) is pointed. It also shows the need of existing algorithms (from irregular sampling) verification. Fifteen years' service knowledge of using mentioned method aboard T-11 "Iskra" is presented.
Źródło:: Biuletyn Wojskowej Akademii Technicznej; 2008, 57, 2; 289-299
1234-5865
Pojawia się w:: Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:: Biblioteka Nauki

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