In view of the urgent demand for wide speed range and high-performance power for next generation aircraft, near space multi-functional platform and the first stage of TSTO (two-stage-to-orbit) transportation system, this paper timely puts forward an innovative turbo-rocket combined cycle propulsion scheme named NUAA-PTRE (Pre-cooled Turbo-Rocket Engine designed by Nanjing University of Aeronautics and Astronautics) under Ma 0–5. In the scheme, hydrocarbon fuel at normal temperature is employed to pre-cool incoming air, and the chemical heat sink of fuel cracking is utilized sufficiently, which expends flight Mach number range of aircraft effectively. In this paper, the performance characteristics of the engine such as thrust, specific impulse under Ma 0–5 and 0–30km in the flight envelope are studied. The influence of air pre-cooling on the performance at Ma 4–5 is evaluated. This paper points out that the pre-cooling of incoming air by pyrolysis of endothermic hydrocarbon fuel above Ma 4/880 K can broaden the working Mach number range of the engine and improve the performance of the engine at high Mach number. The pre-cooled turbo-rocket combined cycle propulsion scheme of NUAA-PTRE, proposed in this paper meets the working requirements of full speed range from Ma 0–5 and full airspace from 0–30 km, and can be used to support the application of next generation aircraft.

针对下一代飞行器、近空间多功能平台、TSTO（两级入轨）运输系统第一级对宽航速和高性能动力的迫切需求，本文适时提出了Ma 0-5下的创新涡轮火箭联合循环推进方案，命名为NUAA-PTRE（南京航空航天大学设计的预冷涡轮火箭发动机）。该方案采用常温碳氢燃料对来风进行预冷，充分利用燃料裂解的化学散热器，有效扩展了飞机的飞行马赫数范围。本文研究了发动机在飞行包线内Ma 0-5和0-30km下的推力、比冲等性能特性。评估了空气预冷对 Ma 4-5 性能的影响。本文指出，在Ma 4/880 K以上通过热解吸热碳氢燃料对进气进行预冷，可以拓宽发动机的工作马赫数范围，提高发动机在高马赫数下的性能。本文提出的NUAA-PTRE预冷涡轮火箭联合循环推进方案满足马0-5全速范围和0-30公里全空域的工作要求，可用于支持应用下一代飞机。