适应飞机需求的进气预冷技术路线分析

Technical Route Analysis of Intake Precooling Adapted to Aircraft Requirements

为了综合评价高超飞机用高Ma的涡轮发动机及其组合动力的预冷技术方案,从工程应用角度以飞机动力需求为牵引,开展了射流预冷、超临界氦强预冷和燃油强预冷技术方案的对比分析。针对3种预冷技术方案的原理、技术优势、存在的问题,以及适应飞机需求的标志性技术指标开展分析和评估,从跨速域时性能、技术难度及风险、付出的成本代价和周期,以及发展前景等方面开展了综合分析。结果表明:从满足产品需求的角度出发,与超临界氦强预冷和燃油强预冷技术方案相比,射流预冷技术装置结构简单、可靠性高、总压损失小、可与进气道高度集成、供水量适度,以及涡轮发动机本身提供的功率足以驱动射流预冷系统无需额外能源,是目前涡轮发动机扩包线的较优方案。

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-speeddomain 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.