Analysis of a metal matrix composite heat exchanger for a hypersonic engine

Hypersonic vehicles are being investigated for commercial and defense missions by the aerospace, government, and academic communities. Vehicle velocities will result in extreme heating of the outer surfaces and engine panels. Vehicle weight is critical; use of conventional design practices and materials will result in a vehicle too heavy to lift off. Actively cooled panels using advanced material will be required for surfaces subjected to extremely high heat fluxes. A study was performed for one type of advanced material for such a high heat flux area. The specific area studied was the combustor sidewall of a hypersonic engine. An advanced fiber-reinforced metal matrix composite, copper graphite (Gr/Cu), was selected as the heat exchanger material. Several heat exchanger configurations have been evaluated before selection of one for detailed analysis. The goal of this study was to demonstrate analytical techniques for determining stresses, strains, and panel deflections applicable to a metal matrix composite heat exchanger. Limitations as to analytical accuracy and applicability are presented.