PL EN


Preferencje help
Widoczny [Schowaj] Abstrakt
Liczba wyników
Tytuł artykułu

Experimental Crack Propagation Analysis of the Compressor Blades Working in High Cycle Fatigue Condition

Autorzy
Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
This paper presents results of experimental vibration tests of the helicopter turbo-engine compressor blades. The blades used in investigation were retired from maintenance under technical inspection of engine. Investigations were conducted for selected undamaged blades, without existence of preliminary cracks or corrosion pits. The blades during experiment were entered into transverse vibration. The crack propagation process was conducted in resonance condition. During the fatigue test, the growth of crack was monitored. In the second part of work, a nonlinear finite element method was utilized to determine the stress state of the blade during vibration. In this analysis a first mode of transverse vibration were considered. High maximum principal stress zone was found at the region of blade where the crack occurred.
Rocznik
Tom
Strony
195--204
Opis fizyczny
Bibliogr. 17 poz., fot., rys., tab., wykr.
Twórcy
autor
  • Rzeszów University of Technology Rzeszów, Poland
Bibliografia
  • [1] Lourenço, N. J., Graça, M. L. A., Franco, L. A. L., & Silva, O. M. M. (2008). Fatigue failure of a compressor blade. Engineering Failure Analysis. 15, 1150-1154.
  • [2] Kermanpur, A.; Sepehri Ami, H.; Ziaei-Rad, S., Nourbakhshnia, N., Mosaddeghfar, M. (2008). Failure analysis of Ti6Al4V gas turbine compressor blades, Engineering Failure Analysis. 15, 1052-1064.
  • [3] Silveira, E., Atxaga, G., & Irisarri, A.M. (2008). Failure analysis of a set of compressor blades. Engineering Failure Analysis. 15, 666-674.
  • [4] Poznanska, A., Sniezek, M., & Wierzbinska, M. (2003). Pitting corrosion - main factor generating fracture of the compressor of aeroengine blades under operation [in Polish]. In: Proceedings of the IX Conference - Turbomachinery. Rzeszow.
  • [5] Troshchenko, V.T., & Prokopenko, A.V. (2000). Fatigue strength of gas turbine compressor blades. Engineering Failure Analysis. 7, 209-220.
  • [6] Park, M., Hwang, Young-H., Choi, Y.-S, & Kim, T.-G. (2002). Analysis of a J69-T-25 engine turbine blade fracture, Engineering Failure Analysis. 9, 593-601.
  • [7] Song K.-S., Kim, S.-G., Jung, D., & Hwang Y.-H. (2007). Analysis of the fracture of a turbine blade on a turbojet engine, Engineering Failure Analysis. 14, 877-883.
  • [8] Vardar N., Ekerim A. (2007). Failure analysis of gas turbine blades in a thermal power plant. Engineering Failure Analysis. 14, 743-749.
  • [9] Xu X., & Yu Z. (2007). An investigation on the failed blades in a locomotive turbine. Engineering Failure Analysis. 14, 1322-1328.
  • [10] Song, K., Kim, S., Jung, D., & Hwang,Y. (2007). Analysis of the fracture of a turbine blade on a turbojet engine Engineering Failure Analysis. 14, 877-883.
  • [11] Xie, Y. et al. (2006). Analysis of superalloy turbine blade tip cracking during service, Engineering Failure Analysis, 13, 1429-1436.
  • [12] Witek, L. (2006). Failure analysis of turbine disc of an aero engine, Engineering Failure Analysis, 13(1). Elsevier Science.
  • [13] Witek, L., Kowalski, T., & Mamrowicz, J. (2007). Numerical stress and fatigue analysis of the first stage of turbine for helicopter engine. In: Proceedings of the International Conference on Aeronautical Fatigue, Napoli.
  • [14] Witek, L, Poznańska, A., & Wierzbińska, M. Fracture analysis of a compressor blade of an helicopter engine. Engineering Failure Analysis. 16(5), 1616-1622.
  • [15] MSC Corporation. (2004). MSC-PATRAN User_s Manual, ver. 2004. Los Angeles: MSC Corporation.
  • [16] Michailov, P. B. (1961). Sprawocznik po Metaliczeskim Matierialam Turbino- i Motorostroenija, Petersburg.
  • [17] Dessault Systems. (2007). ABAQUS Users Manual, ver. 6.7. Abaqus Inc.
Uwagi
EN
This work was supported by Polish Ministry of Science and Higher Education (Project no. NN 504346736).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-5a005020-4c45-4130-a865-1a3351d6856d
JavaScript jest wyłączony w Twojej przeglądarce internetowej. Włącz go, a następnie odśwież stronę, aby móc w pełni z niej korzystać.