Failure analysis of compressor first stage rotor blades of an aeroengine

Bhaumik, SK (2004) Failure analysis of compressor first stage rotor blades of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.

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Abstract

All the four 1st stage compressor rotor blades belonging to an aeroengine have failed by fatigue. The fatigue cracks have initiated at the edge of the locking plate slot on the convex side of the blade. The tensile stress along the edges of the slots arising due to restriction in the movement of the blades while attaining the stable position appears to be the most probable reason for the fatigue crack initiation. Use of locking plate made of a softer material such as stainless steel of grade S-526 (hardness less than RC 20) is suggested to avoid the recurrence of similar failure. A detailed analysis is presented in this report.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aeroengine;compressor first stage rotor blades;fatigue;locking plate material
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division
Depositing User: Mrs Manoranjitha M D
Date Deposited: 27 Jul 2011 14:12
Last Modified: 27 Jul 2011 14:12
URI: http://nal-ir.nal.res.in/id/eprint/9703

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