Failure analysis of compressor stator and rotor blades of an aeroengine

Madan, M and Suresh Kumar, M and Venkataswamy, MA and Sujata, M and Parameswara, MA and Bhaumik, SK (2005) Failure analysis of compressor stator and rotor blades of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.

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The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades were found to have failed by fatigue. The fatigue cracks in the stator blades have initiated at the under cut of the leading edge hub. Stress concentrators such as rough filing marks and rough EDM surface were found responsible for the fatigue crack initiation. In the case of rotor blades, fatigue cracks initiated from either side of the airfoil with multiple origins and propagated to form through thickness cracks. No metallurgical abnormalities were responsible for fatigue crack initiation and hence fatigue appears to be stress related. Evidences suggest that tip rubbing with the casing would have caused excessive bending stresses on the blade resulting in fatigue crack initiation.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aeroengine;compressor stator blades;rotor blades;fatigue;stress concentrators;blade tip rub
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Mrs Manoranjitha M D
Date Deposited: 02 Nov 2011 05:56
Last Modified: 02 Nov 2011 05:56

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