Failure analysis of low-pressure turbine rotor blade of an aeroengine

Madan, M and Bhuvana, R and Sujata, M and Venkataswamy, MA and Bhaumik, SK (2008) Failure analysis of low-pressure turbine rotor blade of an aeroengine. Project Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

Fractographic study showed that the blade bearing No. HAEE 20 has failed by fatigue. The fatigue crack was found to have initiated at the leading edge, slightly towards convex surface, over a length of about 200 m. After initiation, the crack has propagated progressively over about 40 to 50 % of the blade cross section before giving way to final static overload fracture. Examination revealed delamination/cracking of the coating at the fatigue crack origin. A few intergranular cracks were also found present in the blade material in this region. Evidences suggest that most probably, the cracks got generated first in the coating and in the adjacent region of the blade material, and the stress raisers thus resulted were responsible for the subsequent transgranular fatigue crack initiation. It needs to be examined whether or not the past history of the engine has any influence on the initial crack generation in the coating and the blade material. It is confirmed that the damages observed in other LPTR blades or engine parts are secondary in nature and have occurred subsequent to the primary failure in blade HAEE 20. A detailed analysis of the failure is presented in this report.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aeroengine;LPTR 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: Ms. Alphones Mary
Date Deposited: 19 Jul 2011 10:23
Last Modified: 19 Jul 2011 10:23
URI: http://nal-ir.nal.res.in/id/eprint/9447

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