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Structural analyses of engine wall cooling concepts and materialsThe severe thermal environments under which hypersonic aircraft such as the National Aerospace Plane (NASP) will operate require cooling of the engine walls, especially in the combustor. A preliminary assessment is made of some candidate materials based on structural analyses for a number of convective cooling configurations. Three materials were studied: graphite/copper and tungsten/copper composite alloys with 50 percent fiber volume fractions and a wrought cobalt-base superalloy, Haynes 188. Anisotropic mechanical and thermal properties for the composites were obtained from a computer code, ICAN, which determines the composite material properties from the individual properties of the fiber and matrix materials. The structural analyses were performed by using the MARC nonlinear finite element code. Heat transfer analyses were conducted to calculate the metal temperature distributions.
Document ID
19880013021
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaufman, Albert (Sverdrup Technology, Inc. Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1988
Publication Information
Publication: NASA. Lewis Research Center, Lewis Structures Technology, 1988. Volume 2: Structural Mechanics
Subject Category
Composite Materials
Accession Number
88N22405
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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