ZHANG Yan-jun 1 , LIU Tai-qiu 1 , HU Peng-fei 2 , YU Xue-ming 1.Technical Route Analysis of Intake Precooling Adapted to Aircraft Requirements[J].航空发动机,2024,50(2):58-64
Technical Route Analysis of Intake Precooling Adapted to Aircraft Requirements
DOI:
Key Words:combined propulsion  intake precooling  Mass Injection and Pre-compressor Cooling (MIPCC)  deep precooling  aeroengine  technical route
Author NameAffiliation
ZHANG Yan-jun 1 , LIU Tai-qiu 1 , HU Peng-fei 2 , YU Xue-ming 1 1. AECC Shenyang Engine Research InstituteShenyang 110015China 2. Chinese Aeronautical EstablishmentBeijing 100029China 
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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.
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