Purwar, Anupam and Mahapatra, D R (2016) Design of Thermal Barrier Coating System for Scramjet using Coupled Thermo-Structural Analysis. In: TRANSACTIONS OF THE INDIAN CERAMIC SOCIETY, 75 (4). pp. 242-249.Full text not available from this repository. (Request a copy)
Thermal barrier coating (TBC) is essential for scramjet structure to protect the metallic structure from melting or developing high stress. In this perspective, a novel TBC system with multiple layers of ceramics: top layer, intermediate layer, bond coat over a suitable metal substrate has been proposed. First, material selection for TBC system has been carried out based on their thermal conductivity and maximum operational temperature. Then, an elaborate design methodology has been evolved to constrain the temperature of each layer within their operational limit and minimization of thermal mismatch. Different design parameters have been identified and iterative finite element based thermo-structural analyses have been carried out to optimize them and hence, limit metal substrate temperature within 1250 K and the maximum interfacial shear stress within 80 MPa, when exposed to heat flux as high as 1.5 MW/m(2) and pressure greater than 1.3 bars.
|Item Type:||Journal Article|
|Additional Information:||Copy right for this article belongs to the INDIAN CERAMIC SOC, CENTRAL GLASS & CERAMIC RES INST, KOLKATA, 700 032, INDIA|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||15 Mar 2017 04:53|
|Last Modified:||15 Mar 2017 04:53|
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