基于飞发一体化模型的射流预冷技术优势分析

In order to explore the application prospect of mass injection pre-compressor cooling technology in advanced aero-engines in the future，a simulation model of aircraft-engine integration was built based on turbojet engine， water was selected as the coolant， and the effects of different flight conditions and precooling schemes on aircraft combat capability，engine performance and temperature of hot end component were analyzed. The results showed that the thrust of aero-engine can be increased by mass injection pre-compressor cooling technology， which can improve the climbing and acceleration performance of aircraft and reduce the mission time and load consumption within the assigned task. The surface temperature of turbine blade can be also decreased with the reduction of the temperature of bleed air due to mass injection pre-compressor cooling technology. Given the matching principle of aircraft-engine thrust and the constraint of the surface temperature of turbine blade，the ultimate flight performance of aircraft can be improved effectively by mass injection pre-compressor cooling technology. If the flow rate of coolant was 1 kg/s，the theoretical ceiling and maximum Mach number of aircraft can be increased by 11.67% and 10.51%，respectively.