射流冷却对航空发动机压气机的特性分析

Considering the high-temperature inlet air of aero-engines at a high Mach number, this study establishes a mathematical model of air-mist evaporative cooling in a compressor coupled with a pre-cooling section under a high-altitude environment, which is based on the Eulerian-Lagrangian multi-phase flow method. The compressor characteristics were analyzed under different spray conditions and high-altitude environments. The results show that massive injection cooling could increase the intake flow rate, suppress the temperature rise, and increase the total pressure ratio in a high-altitude high-Mach environment. Within a certain range, larger water injection rate and smaller droplet size were conducive to reducing the total temperature ratio and increasing the total pressure ratio, as well as reducing the compressor's compression power consumption and increasing efficiency. Therefore, the aero-engine compressor characteristics can be effectively improved by the addition of a pre-cooling section for inlet air cooling.