Failure analysis of HP Turbine blades pertaining to an aeroengine.

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.

Full text not available from this repository. (Request a copy)

Abstract

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.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: HP turbine blades;aeroengine;high temperature;oxidation;hot gas erosion
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, Materials Science Division
Depositing User: Mrs Manoranjitha M D
Date Deposited: 05 Dec 2011 16:49
Last Modified: 05 Dec 2011 16:49
URI: http://nal-ir.nal.res.in/id/eprint/10126

Actions (login required)

View Item