针对一种小型涡喷发动机和脉冲爆震发动机(PDE)的混合推进系统,介绍了其结构组成及工作过程,建立了性能计算的简化数学模型,分析了其飞行性能及涡喷发动机效率特性的影响。结果表明,为降低耗油率,提高单位推力,涡喷发动机最佳增压比为5~8,最佳涡轮前燃气温度为1200~1300K;保持PDE进口压力不变,随着飞行马赫数的提高和飞行高度的降低,发动机推力下降,总耗油率升高;随着压气机和涡轮效率的降低,PDE单位推力变化不大,耗油率明显升高。

Firstly, primary structure and operation process of a hybrid propulsion system of small-scale turbojet engine and pulse detonation engine (PDE) were introduced.Secondly, the simplified mathematical model was established to calculate its performance.Finally, fight performance and effect of efficiency characteristics of turbojet engine were analyzed.Results indicate that the optimal compressor ratio is 5 ~8, and the optimal turbine inlet temperature is 1 200~1300 K to reduce the specific fuel consumption and to increase the specific thrust.Presetting the inlet pressure of PDE as const, thrust decreases and total specific fuel consumption increases with Mach increasing and flight altitude decreasing; Specific thrust of PDE shows little change but total specific fuel consumption shows significant rise when efficiency of compressor and turbine decreases.