Ray, A K and Tarafder, S and Das, D K and Venkatraman, B and Roy, P K and Goswami, B and Tiwari, Y N and Palit Sagar, S and Ranganath, V R and Das, Goutam and Chaudhuri, S and Ghosh, R N (2004) Damage resistance of thermal barrier coated superalloy in combustion chamber liner. Journal of Metallurgy and Materials Science, 46 (4). pp. 205-212.
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This paper highlights the high temperature high cycle fatigue and accelerated creep properties of thermal barrier coated (TBC)Superni C263 alloy used as candidate material in combustion chamber liner of aero engines. Results reveal that the endurance limit in fatigue and the life of TBC coated composite under accelerated creep conditions are substantially high than those of the sub-strate material. Fractographic features at high stresses under fatigue was intergranular cleavage where as those at low stresses were transgranular and ductile in nature. Delamination of the bond coat and spallation of the TBC at high stresses during fatigue was evident.
|Uncontrolled Keywords:||Thermal barrier coating; substrate; fatigue; creep|
|Divisions:||Material Science and Technology|
|Deposited By:||Dr. A K Sahu|
|Deposited On:||27 Apr 2012 10:53|
|Last Modified:||27 Mar 2018 10:04|
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