Abstract: In this paper is presented an analysical method for supersonic combustor study, which is based on the Billig model and AHHYMKNH formula.As example,the operating regime,wall profile and performance parameters of supersonic combustors with entry Mach number 2.2 are computed in some detail. Some useful information for supersonic combustor design has been obtained.

Key words: Supersonic combustion ramjet engine;Combustor;Computation;Space shuttle main engine

摘要： 本文以Billig模型和公式为基础,给出了超音燃烧室的分析计算方法;并以燃烧室的进口马赫数是2.2为例,对燃烧室的工况、壁型及参数变化进行了详细的分析研究。所得结论,有助于对超音燃烧室的理解和设计。

关键词: 超音速燃烧冲压式喷气发动机;燃烧室;计算;航天飞机主发动机