涡轮基组合循环发动机推力陷阱问题解决方案  

Overview of solutions to TBCC engine thrust trap problem

作　　者：郑日恒 陈操斌 ZHENG Riheng;CHEN Caobin(School of Energy and Power Engineering,Beihang University,Beijing 100083,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083 [2]北京动力机械研究所,北京100074

出　　处：《火箭推进》2021年第6期21-32,共12页Journal of Rocket Propulsion

摘　　要：涡轮基组合循环(TBCC)发动机模态转换过程中推力陷阱问题需要得到解决。对比了国内外TBCC发动机推力陷阱问题的解决方案,分析了不同方案在选择时需要考虑的主要影响因素。结果表明,变循环方案是以几何调节延缓涡轮发动机推力衰减来解决陷阱问题;而预冷方案和火箭助力方案是以大幅提高发动机整机推力来解决推力陷阱问题。TBCC发动机推力陷阱解决方案的选择,与飞行器的任务需求、发动机性能、燃料选择及技术成熟度等多重要素相关联,需要根据飞行器的具体要求及自身技术积累权衡确定。预冷方案可望在TBCC发动机中得到应用。The problem of thrust trap during mode transition for turbine based combined cycle(TBCC)needs to be solved.Different solutions to the thrust trap problem of TBCC engine are reviewed and compared in this paper.The basic principles and key technologies of different solutions are compared,and the main factors that should be considered in the selection of solutions are presented.The results show that the variable cycle scheme solves the trap problem by delaying the turbine engine thrust attenuation with geometric adjustment.And the pre-cooling scheme and the rocket-boosted scheme solve the thrust trap problem by greatly increasing the thrust of the engine.The choice of TBCC engine thrust trap solution is related to the mission requirements,engine performance,fuel selection and technology maturity and so on,which need to be determined according to the specific requirements of the aircraft and its own technology accumulation.It is hopeful that the pre-cooling technology may be applied in TBCC engine.

关 键 词：TBCC 推力陷阱 变循环 预冷 火箭助力 高超声速 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]