Composite Wall Concept for High-Temperature Turbine Shrouds–Heat Transfer Analysis 801138
A heat transfer analysis was made of a composite wall shroud consisting of a ceramic thermal barrier layer bonded to a porous metal layer which, in turn, is bonded to a metal base. The porous metal layer serves to mitigate the strain differences between the ceramic and the metal base. Various combinations of ceramic and porous metal layer thicknesses and of porous metal densities and thermal conductivities were investigated to determine the layer thicknesses required to maintain a limiting temperature in the porous metal layer. Analysis showed that the composite wall offered significant air cooling flow reductions compared to an all-impingement air-cooled all-metal shroud.
Citation: Ludwig, L. and Stepka, F., "Composite Wall Concept for High-Temperature Turbine Shrouds–Heat Transfer Analysis," SAE Technical Paper 801138, 1980, https://doi.org/10.4271/801138. Download Citation
Author(s):
Lawrence P. Ludwig, Francis S. Stepka
Affiliated:
NASA-Lewis Research Center, Cleveland, OH
Pages: 12
Event:
Aerospace Congress and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Heat transfer
Ceramics
Metals
Composite materials
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