在高马赫数飞行时,进气总温过高会导致压气机性能严重恶化,射流预冷湿压缩可降低进口空气总温,降低压气机功耗,提高循环效率。本文以跨声速压气机级NASA Stage35为研究对象,建立基于欧拉-拉格朗日法的压气机气液两相三维流场计算方法,从压气机内部流场变化、轴向位置温度分布、压气机性能角度出发,研究高速涡轮机压气机内射流预冷湿压缩性能及流动换热特性。研究表明：在流动换热方面,射流预冷湿压缩可使叶片前缘及叶片尾缘后的高温区域温度明显降低,激波下游的低速区减小。液滴直径的减小,喷液量的增加,飞行马赫数的提高,均可提升压气机的降温效果,温度最大可降98 K~54 K。在性能方面,射流预冷湿压缩能明显提高进口流量,降低压气机比压缩功,提升压气机效率；液滴直径越小,喷液量越大,压气机的效率越大,效率较干压缩最大提高6%~10%；且随着马赫数的增加,液滴直径对压气机性能的影响变小。

During flight under high Mach number, air compressor suffers from a serious performance deterioration due to the high total temperature of inlet air. Mass injection pre-cooling can reduce the total temperature of inlet air, lower the power consumption of the compressor, and improve the cycle efficiency. A NASA Stage 35 transonic compressor is analysed by a two-phase calculation based on Euler-Lagrange method from aspects of flow field change, axial po-sition temperature distribution and the performance of compressor. From the aspect of flow and heat transfer, the research shows that mass injection pre-cooling wet compression can significantly reduce the temperature of the hot spot around leading edge and behind trailing edge, with the temperature of compressor flow field reduced by a maximum of 98 K~154 K by three approaches of decreasing the droplet diameter, increasing the mass flow rate of injected coolant, and increasing Mach number of flight. From the aspect of compression performance, the research shows that mass injection wet compression can increase the mass flow rate of inlet air, and increase the efficiency of compressor by a maximum of 6%~10% by two approaches of increasing the mass flow rate and decreasing the droplet diameter, which is a less significant under high Mach number.

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航空发动机气动热力国防科技重点实验室基金项目（2023-JCJQ-LB-063-0407）