Failure analysis of 1st stage compressor rotor blades of an aeroengine

Bhaskaran, TA and Venkataswamy, MA and Sujata, M and Keshab, Barai and Bhaumik, SK (2003) Failure analysis of 1st stage compressor rotor blades of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.

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Abstract

Blade No. 192 of the 1st stage compressor rotor of an aeroengine had failed by fatigue. The fatigue appears to be of high cycle – low stress type and stress related. It appears most probable that due to modification at the base of the blades, the movement of the blades during engine run was restricted. This might have resulted in improper butting of the dovetail flank of the blades with the disc resulting in fatigue crack initiation. The rubbing at the tip of the blades is secondary in nature and subsequent to the primary fatigue failure of blade No. 192.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aeroengine;compressor rotor blade;fatigue
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division, Materials Science Division, Materials Science Division, Materials Science Division, Materials Science Division
Depositing User: Mrs Manoranjitha M D
Date Deposited: 05 Aug 2011 14:50
Last Modified: 05 Aug 2011 14:50
URI: http://nal-ir.nal.res.in/id/eprint/9815

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