Ray, Ashok K and Roy, Nilima and Dash, Byomkesh and Das, D K and Ranganath, V R and Goswami, B and Singh, M P and Tiwari, Y N and Roy, P K and Das, H K and Sanyal, D and Dwarakadasa, E S (2006) High temperature mechanical properties of thermal barrier coated superalloy applied to combustor liner of aero engines. High Temperature Materials And Processes , 25 (3). pp. 109-119.
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High temperature load controlled fatigue, hot tensile and accelerated creep properties of thermal barrier coated (TBC) Superni C263 alloy used as a candidate material in combustor liner of aero engines are highlighted in this paper. Acoustic emission technique has been utilised to characterise the ductile-brittle transition temperature of the bond coat. Results revealed that the DBTT (ductile to brittle transition temperature) of this bond coat is around 923 K, which is in close proximity to the value reported for CoCrAlY type of bond coat. Finite element technique, used for analysing the equivalent stresses in the bond coat well within the elastic limit, revealed the highest order of equivalent stress at 1073 K as the bond coat is ductile above 923 K. The endurance limit in fatigue and the life of TBC coated composite under accelerated creep conditions are substantially higher than those of the substrate material. Fractographic features at high stresses under fatigue showed intergranular cleavage whereas 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. Unlike in the case of fatigue, the mode of fracture in the substrate at very high stresses was transgranular whereas that at low stresses was intergranular in creep.
|Uncontrolled Keywords:||thermal barrier coating; substrate; fatigue; creep; tensile; finite element; fractography; trans-granular; intergranular; spallation|
|Divisions:||Material Science and Technology|
|Deposited By:||Sahu A K|
|Deposited On:||19 Jul 2011 12:18|
|Last Modified:||08 Feb 2012 16:25|
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