Abstract: The key technical difficulties and performance of the TRRE were studied. A brief introduction was conducted on the progress of the principle prototype from the Beijing Power Machinery Institute. The performance data from the flow channel design of the principle prototype and numerical simulations were utilized to assess the propulsion performance of the TRRE engine，which primitively validated its comprehensive advantages on the acceleration，cruising，mobility and other aspects. The results show that the TRRE engine can reconcile the demands of high thrust at lower Mach numbers and high specific impulse at a Mach number of 6.0 (pure scramjet mode). In a wide Mach number operating range，the TRRE engine provides the relatively wide，flexible and convenient adjustment ability in the thrust. It can satisfy the smooth relay between the high and low speed channels，illustrating the advantageous adaptability in the acceleration，maneuver flight and high Mach number cruising.

Key words: Near space and aerospace vehicle；Combined engine；Performance analysis

摘要： 对TRRE发动机关键技术难点及技术途径进行了初步分析，对北京动力机械研究所原理样机研制进展进行了简要介绍，并结合原理样机流道设计与数值仿真研究获得的性能数据，开展了TRRE发动机推进性能探索研究，初步验证了TRRE发动机在兼具加速、巡航、机动等方面的性能优势。研究结果表明，在适当兼顾低马赫数大推力需求和Ma=6纯冲压工况高比冲需求的情况下，发动机在宽马赫数工作范围具有较大范围、灵活便捷的推力调节能力，可满足高低速通道平稳接力需求，表现出极具优势的加速、机动飞行和高马赫数巡航的适应性。

关键词: 临近空间及空天飞行器；组合发动机；性能分析