Investigation of first stage compressor rotor blade of an aeroengine

Suresh Kumar, M and Madan, M and Venkataswamy, MA and Sujata, M and Parameswara, MA and Bhaumik, SK (2005) Investigation of first stage compressor rotor blade of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.

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The compressor rotor blade in question had failed by fatigue. There were two fatigue cracks in the airfoil of the blade: one in the longitudinal direction and the other, in the transverse direction of the blade airfoil. Analysis shows that a longitudinal crack had developed on the concave surface of the airfoil probably due to tip rubbing. It appears that once the tip clearance was established by wear, this crack had ceased to propagate. Subsequently, another fatigue crack had initiated on the existing longitudinal crack due to notch effect, which eventually propagated progressively through the blade thickness leading to fracture. The microstructure and the composition of the blade material conform to Ti-alloy of IMI 550 specification. No metallurgical and/or mechanical abnormalities were responsible for the fatigue crack initiation.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aeroengine;compressor rotor blade;fatigue;tip rubbing
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Mrs Manoranjitha M D
Date Deposited: 24 Aug 2011 08:14
Last Modified: 24 Aug 2011 08:14

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