Abstract: A fixed geometric,dual mode supersonic combustor was selected and the thermodynamic adjustment method,which means the adjustment of the way of fuel injection and heat release rate of combustion,was adopted to realize dual mode combustion with a wide range Mach number.One dimensional constant specific heat model was taken to analyze the influence of the related parameters on the combustion mode transition and the combustor performance.The interaction between the isolator and the combustor was also analyzed.The results demonstrate that the thermodynamic adjustment method is viable to be adopted to realize the combustion mode transition in a supersonic combustor.

Key words: Supersonic combustion ramjet engine;Supersonic combustion;Subsonic combustion;Ram air combustor;Performance analysis

摘要： 选择了固定几何流通截面的双模态超燃燃烧室模型，采用气动热力调节的方法（即调节燃料喷射方式和燃烧速率）来实现双模态、宽马赫范围工作。在计算中用一维、定比热容方法分析了相关参数对燃烧室模态转变、性能的影响和隔离段与燃烧室的相互作用。计算结果表明，气动热力调节实现燃烧室内燃烧模态的转变是可行的。

关键词: 超音速冲压喷气发动机;超音速燃烧;亚音速燃烧;冲压进气燃烧室;性能分析