Failure analysis of a 3rd stage compressor stator blade

Suresh Kumar, M and Sujata, M and Madan, M and Venkataswamy, MA and Bhaumik, SK (2006) Failure analysis of a 3rd stage compressor stator blade. Project Report. National Aerospace Laboratories, Bangalore, India.

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The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on the convex and concave surface of the airfoil. After initiation, these cracks have propagated simultaneously and finally, joined together resulting in fracturing of the blade. Evidences suggest that there were enumerable number of preexisting cracks on the blade airfoil surface that promoted fatigue crack initiation. Analysis showed that excessive twisting of the blade at the leading edge tip could be one of the probable reasons for generation of such array of cracks. The microstructure and hardness of the blade material were found to be satisfactory, and no metallurgical abnormalities were responsible for the failure.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aeroengine;Compressor stator blade;Failure;Fatigue;Blade twisting
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Ms. Alphones Mary
Date Deposited: 29 Jul 2011 05:45
Last Modified: 29 Jul 2011 05:45

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