Abstract: A simple thermodynamic calculation method is introduced and some calculative results of fan-ramjet are presented with fan-pressure-ratio (FPR) of 3 along trajectory of constant dynamic pressure of 0.7. The FPR does show important effect on altitude thrust and take-off thrust/weight ratio (TWR) . The effect of trajectories and angle of attack on engine performance are included in analysis and water injection into engine at M≥6 may be able to extend ramjet working till M = 7.5.

Key words: Turbofan engine;Ramjet engine;Aerospace plane;Computation

摘要： 本文介绍了涡轮风扇冲压组合发动机的一种简化的热力性能计算方法及风扇压比为3的风扇冲压发动机沿等动载((?)=0.7)轨迹飞行时发动机性能计算结果。文章着重分析了风扇压比对发动机高空推力及起飞推重比的影响,还分析了大飞行动载及高飞行攻角对发动机性能的有利影响。最后,对发动机在M≥6之后采用注水加力方法提高亚燃冲压发动机工作上限问题进行了研究。

关键词: 涡轮风扇发动机;冲压式喷气发动机;航空航天飞机;计算