射流预冷却吸气式涡轮火箭发动机性能模拟  

Performance simulation of air-turbo-rocket with water injection pre-cooler

作　　者：李成[1] 蔡元虎[1] 屠秋野[1] 孙泽晖[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2011年第1期1-4,31,共5页Journal of Propulsion Technology

基　　金：教育部高校博士点新教师基金(200806991061);航空科学基金(2008ZB53014);国家自然科学基金(50906071);陕西省自然基金(SJ-08-ZP06)

摘　　要：为扩展吸气式涡轮火箭发动机工作范围,提高发动机性能,在常规涡轮火箭发动机基础上加入射流预冷系统并修改热力模型,建立了射流预冷却吸气式涡轮火箭发动机性能计算模型。在给定航迹和控制规律下分析了不同压气机进口限制温度对喷水量、净推力和比冲的影响。仿真结果显示加入射流预冷器可以极大的扩展涡轮火箭发动机的工作范围,在高马赫数下可以极大的提高涡轮火箭发动机的净推力。In order to expand the operation range and improve the engine performance of air-turbo-rocket,based on the normal air-turbo-rocket with a water injection pre-cooler system and a modified thermodynamic model,a numerical model to calculate air-turbo-rocket performance was set up.On the given flight track and control law,the influence of limited compressor inlet temperature to the water amount,net thrust and specific impulse was analyzed.The results of simulation showed that the operation range was greatly expanded and net thrust was increased at high Mach number by adding a water injection pre-cooler system to the normal air-turbo-rocket engine.

关 键 词：空气涡轮火箭发动机 射流 预冷 数学模型 

分 类 号：V438.1[航空宇航科学与技术—航空宇航推进理论与工程]