RBCC引射模态主火箭射流对Fabri壅塞影响研究  

Effect of Primary Rocket Jet on Fabri Choking in RBCC Ejector Mode

作　　者：林彬彬 李世林 唐庆如[1] 付尧明[1] 周俊 Lin Binbin;Li Shilin;Tang Qingru;Fu Yaoming;Zhou Jun(Aviation Engineering Institute,Civil Aviation Flight University of China,Guanghan 618307,China;Aero Engine Maintenance Training Center,Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民用航空飞行学院航空工程学院,广汉618307 [2]中国民用航空飞行学院航空发动机维修培训中心,广汉618307

出　　处：《战术导弹技术》2020年第4期155-160,207,共7页Tactical Missile Technology

基　　金：中国民用航空飞行学院科研基金项目(J2018-10)。

摘　　要：引射模态发动机性能偏低限制了RBCC发动机的应用,为了提高引射抽吸能力和发动机性能,针对地面零速起飞状态,采用包含飞行器前后体的全流道一体化数值模拟方法,研究了主次流总压比对Fabri壅塞和引射抽吸能力的影响。结果表明:当主次流总压比低于25,提高主次流总压比可提高主火箭射流马赫数,引射空气流量可提高56. 4%;当主次流总压比高于33,提高主次流总压比增大了射流欠膨胀程度,挤压引射空气流道,导致引射抽吸能力降低,引射比可降低53. 1%;主次流总压比高于134可产生Fabri壅塞,火箭射流将引射空气流道堵塞,引射空气流量降为零。The lower ejector mode engine performance limits the application of the RBCC engine.In order to improve the ejection capacity and engine performance,the effect of total pressure ratio of primary and secondary flows on Fabri choking and ejection capacity was studied by means of CFD simulation for the whole flow-path including the fore-airframe and aft-airframe of a flight vehicle.The results show that increasing the total pressure ratio could increase the primary rocket jet Ma,thereby increasing the ejection air mass flow by 56.4%,when the total pressure ratio is less than 25.The primary rocket jet with the higher combustor pressure would expand in the ramjet combustor and squirt the secondary ejection air flow path,therefore reduce the ejection capacity when the total pressure ratio is higher than 33,ultimately,the ejection airflow would decrease 53.1%.The primary rocket jet would block the secondary ejection air flow path,therefore the secondary ejection air mass flow reduce to 0,when the total pressure ratio is higher than 134.

关 键 词：火箭冲压组合发动机 推进系统 引射模态 引射比 气动壅塞 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]