Accession Number : ADA111789

Title :   Supersonic Combustor Insulation Ablation Analysis and Tests,

Corporate Author : JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s) : Newman,Robb W ; Fox,Harold G

PDF Url : ADA111789

Report Date : 14 May 1981

Pagination or Media Count : 27

Abstract : The design of passively cooled, hypersonic tactical missiles poses many severe structural problems whose solutions are beyond the current state-of-the-art. Specifically, the heating conditions in the supersonic combustor of such a missile approach those in the throat section of rocket motors but are more damaging to most materials because the flow is oxidizing rather than reducing. Carbon-carbon materials are being considered for the supersonic combustor wall structure because they have attractive strength-weight characteristics at elevated temperatures. Since these materials which form an oxidation resistant layer are also being considered. In order to design such a combustor, the designer must be able to accurately predict the erosion rate of candidate materials so that a realistic balance can be achieved between weight and performance. This paper addresses the problem of thermochemical erosion of graphitic materials, the development of procedures for the analytical prediction of these erosion rates in a combustor environment, and experimental procedures used to validate the analytical model and evaluate candidate combustor liner materials. (Author)

Descriptors :   *Combustors, *Carbon carbon composites, Supersonic combustion ramjet engines, Combustion chamber liners, Oxidation resistance, Graphited materials, Erosion resistance, Thermochemistry, Ablation, Thermal insulation, Surface temperature, High temperature, Heat transfer, Mass transfer

Subject Categories : Laminates and Composite Materials
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE