Abstract: The calculation of thermodynamic and thrust performances for liquid hydrogen ramjet engine with Mach number ranged from 1.5 to 6.5 is performed in this paper. A delicated method of iteration, which considerably simplified the computation of thermodynamic process,is adopted.The evaluation of performance for scramjet with cylindrical combustion chamber is also carried cut. The results show that the cylindershape combustion chamber is not the best design. An adequate divergence for combustion chamber of sera mjet is needed in order to get higher performanee.

Key words: Ramjet engine;Computation;Space shuttle main engine

摘要： 本文对使用液氢燃料冲压发动机在大马赫数范围内的工作特性进行了比较详细的计算与分析。结果表明使用氢燃料直到马赫数达6.5,亚燃冲压仍具有相当好的比冲特性,而使用碳氢燃料在马赫数达4.5以后比冲特性迅速下降。文章还从加热比和单位空气比冲出发讨论了发动机的调节特性,并建议采用较简单的有级调节来代替复杂的无级连续调节方法。本文还对等截面超燃冲压发动机的特性进行了计算,结果表明等截面极限加热并非最佳设计。

关键词: 冲压式喷气发动机;计算;航天飞机主发动机