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

• Autorzy: Witek L.

Identyfikatory

DOI

10.2478/v10164-010-0017-7

• 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.

Słowa kluczowe

EN

compressor blade; failure analysis; crack propagation; vibration; FEM

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2009
• Tom: Iss. 1
• Strony: 195--204
• Opis fizyczny: Bibliogr. 17 poz., fot., rys., tab., wykr.

Twórcy

autor

Witek L.

• Rzeszów University of Technology Rzeszów, Poland

Bibliografia

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Uwagi

EN

This work was supported by Polish Ministry of Science and Higher Education (Project no. NN 504346736).