<abstract xml:lang="en" xmlns="http://www.w3.org/1999/xhtml"><p>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.</p></abstract>

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.

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

Rzeszów University of Technology, Rzeszów, Poland

Fatigue of Aircraft Structures

This paper presents results of experimental vibration tests of the helicopter turbo-engine compressor blades. The blades used in investigation were retired...

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

Online veröffentlicht: 23. Sept. 2010

Seitenbereich: 195 - 204

DOI: https://doi.org/10.2478/v10164-010-0017-7

Schlüsselwörter
Compressor blade, Failure analysis, Crack propagation, Vibration, FEM

This content is open access.

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

Online veröffentlicht: 23. Sept. 2010

Seitenbereich: 195 - 204

DOI: https://doi.org/10.2478/v10164-010-0017-7

SchlüsselwörterCompressor blade, Failure analysis, Crack propagation, Vibration, FEM

This content is open access.

Schlüsselwörter
Compressor blade, Failure analysis, Crack propagation, Vibration, FEM