PL EN


Preferencje help
Widoczny [Schowaj] Abstrakt
Liczba wyników
Tytuł artykułu

The study on algorithm for identification the fatigue crack length of compressor blade based on amplitude-frequency resonant characteristics

Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
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.
Twórcy
autor
  • Rzeszow University of Technology Department of Aircraft and Aircraft Engines Powstańców Warszawy Av, 8, 35-959 Rzeszow, Poland tel.: +48 17 7432346, +48 17 7432348
autor
  • Rzeszow University of Technology Department of Aircraft and Aircraft Engines Powstańców Warszawy Av, 8, 35-959 Rzeszow, Poland tel.: +48 17 7432346, +48 17 7432348
Bibliografia
  • [1]Bednarz, A., Kuźniar, M., Boltynjuk, E., Temperature distribution as a method of measuringcrack length in fatigue tests of compressor blade, Zeszyty Naukowe PolitechnikiRzeszowskiej – Mechanika, 1, Z. 88, 2016.
  • [2]Bednarz, A., Kuźniar, M., Influence of the crack propagation velocity on heat release incompressor blades during fatigue tests, Journal of KONES Powertrain and Transport,Vol. 23, No. 1, pp. 67-74, 2016.
  • [3]Duo, P., Nowell, D., Schofield, J., Layton, A., Lawson, M., Predictive Study of ForeignObject Damage (FOD) to Aero Engine Compressor Blades, 10th National Turbine EngineHCF Conference, 2005.
  • [4]Endoh, M., Matsuda, Y., Matsuki, M., Non-Contact Measurement of Rotating BladeVibrations, International Gas Turbine Congress, pp. 953-960, Tokyo 1983.
  • [5]Kermanpur, A., Sepehri, A., Ziaei-Red, S., Naorbakhshnia, N., Mosaddeghfar, M., FailureAnalysis of Ti6Al4V Gas Turbine Compressor Blade, Engineering Failure Analysis, Vol. 15,pp. 1052-1064, 2008.
  • [6]Nikhamkin, M., Voronov, L., Semenova, I., Foreign Object Damage and Fatigue StrengthLoss in Compressor Blades, Proceedings of ASME Turbo EXPO 2008, Power for Land, Seaand Air GT2008, June 9-13, 2006, ASME paper GT-2008-51493, Berlin, Germany 2008.
  • [7]Nowell, D., Duo, P., Stewart, I., Prediction of Fatigue Performance in Gas Turbine Bladesafter Foreign Object Damage, International Journal of Fatigue, Vol. 25, pp. 964-969, 2003.
  • [8]Szczepanik, R., Studies on Conditions for Suction of Mechanical Debris from AirfieldSurfaces to Intakes of Jet Engines, Warszawa 1978.
  • [9]Szczepanik, R., Spychała, J., Rokicki, E., Przysowa, R., Pawlak, W., Development ofAlgorithms for Signal Processing for to Use them for Assessment of Technical ConditionDemonstrated by Fluid Flow Machines, Studies of ITWL, No. 71/34, 2006.
  • [10] Szczepanik, R., Experimental studies of Dynamic Properties Demonstrated by Rotor Blades under Various Operating Conditions, Scientific Journal, No. 26, ITWL, Warszaw 2010.
  • [11] Witek, L., Wierzbicka, M., Poznańska, A., Fracture Analysis of Compressor Blades of Helicopter Engine, Engineering Failure Analysis, Vol. 16, pp. 1616-1622, 2009.
  • [12] Witek, L., Experimental Crack Propagation and Failure Analysis of the First Stage Compressor Blade Subjected to Vibration, Engineering Failure Analysis, Vol. 16, pp. 2163-2170, 2009.
  • [13] Witek, L., Bednarz, A., Stachowicz, F., Fatigue analysis of compressor blade with preliminary defect, Engineering Failure Analysis, Vol. 58, Part 1, pp. 229-237, 2015.
  • [14] Witek, L., Bednarz, A., Stachowicz, F. Kazarinov, N., Smirnov, I., Crack propagation analysis of compressor blade subjected to resonant vibrations, Proceedings of XLIII International Summer School Conference APM 2015, pp. 473-481, Sankt Petersburg 2015.
  • [15] Witoś, M., Szczepanik, R., Turbine Engine Health/Maintenance Status Monitoring with Use of Phase-Discrete Method of Blade Vibration Monitoring, Solid State Phenomena, Vol. 147-149, 530-541, 2009.
Uwagi
PL
Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-862487ac-7efa-4a62-b84b-1849160d0c43
JavaScript jest wyłączony w Twojej przeglądarce internetowej. Włącz go, a następnie odśwież stronę, aby móc w pełni z niej korzystać.