用于高超声速推进的MHD-Arc-Ramjet联合循环  

MHD-Arc-Ramjet Combined Cycle for Hypersonic Propulsion

作　　者：于达仁[1] 唐井峰[1] 鲍文[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空学报》2007年第4期769-775,共7页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50306003);国家"863"计划(2002AA722105);中国航天科技集团公司航天科技创新基金(CASC0303)

摘　　要：为了提高冲压发动机在更高速度区内的性能,扩展发动机的运行速度范围,需要在并行于发动机的燃烧室处附加一套能量旁路系统。从能量旁路系统技术实现的角度,分析AJAX(俄罗斯学者提出的一种带有能量旁路的冲压发动机)中能量注入方式的缺点,改用电弧式能量注入方式,形成一种新型的高超声速推进系统——磁流体-电弧-冲压发动机(MHD-Arc-Ramjet)联合循环。热力分析表明:MHD-Arc-Ramjet联合循环的单位推力与AJAX是相当的;由于前者可以在更高的温度下进行能量注入,其在单位推力方面是具有优势的。最后对MHD-Arc-Ramjet联合循环的研究工作做了展望。An energy-bypass system located parallel to combustor is applied for the performance improvement at high flight speed and extension of flight envelop. The disadvantage of energy-reintroduction in AJAX, proposed by Russian as a special case of ranjet engine with energy-bypass system, is explored in this paper, and a new hypersonic propulsive system named as MHD-Arc-Ramjet combined cycle is proposed, which uses arc for energy injection. The results of thermodynamic analysis show that the specific thrust of MHD-Arc-Ramjet combined cycle is equivalent to that of AJAX, and the former is superior to the latter when energy is injected at higher temperature in arc. The future work is listed at the end of paper.

关 键 词：航空、航天推进系统 MHD-Arc-Ramjet联合循环 热力性能分析 AJAX 冲压发动机 

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]