基于飞发一体化模型的射流预冷技术优势分析  

Superiority analysis of mass injection pre-compressor cooling technology based on aircraft-engine integration model

作　　者：栗孟晨 徐国强[1,2,3] 闻洁[2,3,4] 庄来鹤 黄聪聪 LI Mengchen;XU Guoqiang;WEN Jie;ZHUANG Laihe;HUANG Congcong(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,Beihang University,Beijing 100191,China;Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;Hangzhou Innovation Institute(Yuhang),Beihang University,Hangzhou 311000,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学航空发动机气动热力国家级重点实验室,北京100191 [3]北京航空航天大学航空发动机研究院,北京100191 [4]北京航空航天大学杭州创新研究院(余杭),杭州311100

出　　处：《航空动力学报》2023年第9期2167-2176,共10页Journal of Aerospace Power

摘　　要：为探索射流预冷技术在未来先进航空动力上的应用前景,基于涡喷发动机建立飞发一体化性能仿真计算模型,并选取水作为预冷剂,分析不同飞行状态与预冷方案对飞机作战性能、发动机热力性能及热端部件温度的影响规律。结果表明:启用射流预冷技术可有效增加发动机推力,提升飞机的爬升性能与加速性能,帮助飞机在规定任务内减少机动时间与载荷消耗,同时预冷技术可提升压气机末级引气冷却品质,从而降低涡轮叶片表面温度,增强发动机可靠性。在飞发推力匹配条件与涡轮叶片表面温度约束下,射流预冷可有效提升飞机的极限飞行能力,当预冷剂流量为1 kg/s时,飞机理论升限与最大马赫数分别提升11.67%和10.51%。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 aircraftengine 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.

关 键 词：飞发一体化 射流预冷 飞行性能 推力 叶片表面温度 

分 类 号：V231.12[航空宇航科学与技术—航空宇航推进理论与工程]