| Abstract:In order to comprehensively evaluate the precooling technical schemes of high Mach turbine engines and their combined
power for hypersonic aircraft, a comparative analysis of Mass Injection and Pre-compressor Cooling (MIPCC), supercritical helium deep
precooling, and fuel deep precooling schemes was carried out from the perspective of engineering application, guided by the aircraft propul?
sion requirements. An analysis and evaluation were conducted on the principles, technical advantages, existing problems, and key technical
indicators suitable for aircraft requirements of three precooling schemes. A comprehensive analysis was conducted in terms of cross-speed-
domain performance, technical difficulty and risks, cost and cycle, development prospects, etc. The results show that, from the perspective
of meeting product requirements, compared with the technical solution of supercritical helium deep precooling and fuel deep precooling,
the MIPCC device has a simpler structure, higher reliability, lower total pressure loss, can be highly integrated with the intake duct, with
moderate water supply. The power provided by the turbine engine itself is sufficient to drive the MIPCC system without additional energy
requirement. It is currently the preferred solution for expanding the envelope of turbine engines. |
