Failure analysis of I stage compressor rotor blades of an aeroengine

Suresh Kumar, M and Madan, M and Venkataswamy, MA and Sujata, M and Bhaumik, SK (2006) Failure analysis of I stage compressor rotor blades of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.

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Two damaged I stage compressor rotor blades along with two locking pins belonging to an aeroengine were forwarded to the laboratory for investigation. Fractographic examination showed that the blade number 24 had fractured by sudden overload such as impact. The fracturing of this blade was secondary in nature and subsequent to the primary failure. Evidences suggest that the dislodgement of blade number 5 was responsible for the engine failure. The dislodgement of the whole blade without any breakage is not possible unless the locking mechanism fails. It appears most probable that in this particular case, this was possible due to an assembly error wherein a locking pin of length 27.0 mm was used against the specification of 32.0 mm.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aeroengine; compressor rotor blade; locking pin; assembly error
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Raghavendra R chandu
Date Deposited: 25 Jul 2011 05:10
Last Modified: 25 Jul 2011 05:10

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