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Failure analysis of HP Turbine blades pertaining to an aeroengine.

IR@NAL: CSIR-National Aerospace Laboratories, Bangalore

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Title Failure analysis of HP Turbine blades pertaining to an aeroengine.
 
Creator Suresh Kumar, M
Madan, M
Venkataswamy, MA
Sujata, M
Parameswara, MA
Bhaumik, SK
 
Subject Aeronautics (General)
Chemistry and Materials (General)
 
Description Two damaged blades of HP turbine pertaining to an aeroengine were analyzed. Examination revealed damages on a localized region of the leading edge and on the concave surface of the airfoil close to the tip. The damages were mainly in the form of loss of thermal barrier coating (TBC) and heat effects. Evidences suggest that the blades were exposed to high temperature probably in excess of the normal operating temperature, which resulted in deterioration of the TBC. Subsequently, the TBC was dislodged by hot gas erosion.
 
Publisher National Aerospace Laboratories
 
Date 2005
 
Type Proj.Doc/Technical Report
NonPeerReviewed
 
Identifier Suresh Kumar, M and Madan, M and Venkataswamy, MA and Sujata, M and Parameswara, MA and Bhaumik, SK (2005) Failure analysis of HP Turbine blades pertaining to an aeroengine. Project Report. National Aerospace Laboratories, Bangalore.
 
Relation http://nal-ir.nal.res.in/10126/