空气涡轮火箭发动机起动过程推进剂供应及尾喷管面积变化规律研究  

Investigations on the effect of propellant supplying and nozzle area variation in the starting process of air turbo rocket

作　　者：赵巍[1,2,3] 刘蕾 胡斌 李龙婷[1,2] 赵庆军[1,2,3] ZHAO Wei;LIU Lei;HU Bin;LI Longting;ZHAO Qingjun(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China;Academy of Astronautics,University of Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院轻型动力创新研究院,北京100190 [3]中国科学院大学航空宇航学院,北京100190

出　　处：《固体火箭技术》2021年第2期179-187,共9页Journal of Solid Rocket Technology

基　　金：国防基础科研基金项目(JCKY2018603C13)。

摘　　要：为了认识固体推进剂空气涡轮火箭发动机推进剂供应快慢和尾喷管面积变化对发动机起动过程产生的影响,采用容积法建立了考虑工质变比热及化学平衡的发动机动态模型,通过给定不同的推进剂供应速率、尾喷管喉部面积大小及尾喷管喉部面积随转速变化速率,模拟了发动机各工况下的起动过程,对比分析了这些参数对发动机起动时间、共同工作线位置的影响规律。研究发现,增加推进剂供应速率会使发动机起动时间降低,但压气机更接近喘振边界,当尾喷管喉部面积较小时,尾喷管会出现壅塞现象,导致压气机喘振。在此基础上,给出了采用较快推进剂供应速率和尾喷管喉部面积随转速升高而增大相结合的调节方法,使压气机在避免喘振的同时远离堵塞边界,实现了发动机的快速安全起动。The aim of the determination is to study effects of propellant supplying rate and tail nozzle area in the starting process of the solid propellant air turbo rocket,an engine dynamic model considering varying specific heat and chemical equilibrium was set up based on the volume method.Starting processes of the engine were simulated under different propellant supplying rates,different nozzle throat areas and changing rates of nozzle throat area along with shaft speed,and then the effects of these parameters on start⁃ing period and the position of common working line are compared and analyzed.The research results indicate that increasing the pro⁃pellant supplying rate can reduce the accelerating period of starting process,but the common work line of engine will move towards the compressor surge line.When the nozzle throat area is smaller than that of its design value,the tail nozzle will be blocked,and then causing compressor surge.On that basis,an adjusting method is put forward by adopting a higher propellant supplying rate com⁃bined with a enlarging the nozzle throat area along with engine shaft speed increasing,so that the compressor can avoid surging and keep away from the choking boundary.Safe and fast starting process of engine is realized.

关 键 词：空气涡轮火箭发动机 起动过程 压气机喘振 尾喷管喉部面积 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]