Failure analysis of HPTR blades of an aeroengine

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

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


The HPTR blades were found to have damages in the form of peeling off of coating and heat effects. The blades were also covered with molten and solidified metal rich in titanium and oxygen. Evidences suggest that severe tip rubbing was responsible for the crack initiation at the coating- base material interface. The crack then propagated along the interface resulting in peeling off of coating. Due to loss of coating, the blade material was exposed to high temperatures with subsequent degradation of the microstructure. There were no abnormalities either in the coating or in the coating-base material interface. The coating thickness was measured to be about 65 m.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aeroengine;HPTR blades;platinum aluminide coating;coating peel off;tip rubbing
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Mrs Manoranjitha M D
Date Deposited: 11 Aug 2011 10:31
Last Modified: 11 Aug 2011 10:31

Actions (login required)

View Item View Item