Metallurgical examination of damaged parts of an engine of crashed aircraft

Bhaumik, SK (2003) Metallurgical examination of damaged parts of an engine of crashed aircraft. Project Report. National Aerospace Laboratories, Bangalore.

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Abstract

Components retrieved from a crashed aircraft were sent to the laboratory for metallurgical examination. Investigation revealed that the LPTR blade has failed by stress rupture. The crack thus generated at the leading edge acted as a notch and led to the fatigue failure of the blade. Microstructural study and hardness measurements on the cross section of the LPTR blade at the location of fracture indicated overheating. The Failure of LPTR blade is the first event in the chain of events which led to the accident of the aircraft. The damages seen on the other components are secondary in nature and subsequent to the primary failure of the LPTR blade.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aircraft;LPTR;stress rupture;fatigue;overheating
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division
Depositing User: Mrs Manoranjitha M D
Date Deposited: 12 Jul 2011 10:36
Last Modified: 12 Jul 2011 10:36
URI: http://nal-ir.nal.res.in/id/eprint/9318

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