Composite Wall Concept for High-Temperature Turbine ShroudsHeat Transfer Analysis NASA-Lewis Research Center, Cleveland, OH

Format:

Conference/Event

Author/Creator:

Ludwig, Lawrence P., author.

Conference Name:

Aerospace Congress & Exposition (1980-10-13 : Los Angeles, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1980

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

801138

Access Restriction:

Restricted for use by site license