高速涡轮发动机射流预冷湿压缩性能及流动换热研究

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 compressed air power consumption of the compressor, and improve the cycle efficiency. Taking a NASA Stage35 transonic compressor as research object, the wet compression performance and flow and heat transfer characteristic of high-speed turbine compressor mass injection pre-cooling is studied by a two-phase 3D flow field calculation method based on Euler-Lagrange method from aspects of internal flow field change, axial position temperature distribution and the performance of compressor. The research shows that from the aspect of flow and heat transfer, mass injection pre-cooling wet compression can significantly reduce the temperature of the hot spot around leading edge and behind trailing edge, and decrease the low speed zone downstream of the shock wave, with the temperature drop percentage of compressor flow field in the maximum range of 13% -20% 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, mass injection wet compression can increase the mass flow rate of inlet air, reduce compressor specific compression work and increase the efficiency of compressor by a maximum of 6% - 10% compared with dry compression by two approaches of decreasing the droplet diameter and increasing the mass flow rate, which is less affected by droplet diameter under high Mach number.