脉冲爆震涡轮发动机原理性试验研究  

Experimental study on the principle of pulse detonation turbine engine

作　　者：李晓丰[1] 郑龙席[1] 邱华[1] 郑华雷[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《实验流体力学》2013年第6期1-5,共5页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金(50906072)

摘　　要：为研究脉冲爆震燃烧室与涡轮及压气机三者相互匹配的详细机理,建立了脉冲爆震涡轮发动机原理性试验系统,其主要由脉冲爆震燃烧室、涡轮增压器、润滑系统、发动机测控系统等组成。在该试验系统上开展了脉冲爆震涡轮发动机原理性试验研究。首次实现了由脉冲爆震燃烧室驱动涡轮,涡轮带动压气机,压气机压缩空气供给爆震室的全闭环自吸气工作模式。试验结果表明:脉冲爆震涡轮发动机能在自吸气模式下持久、稳定地工作,爆震室与涡轮及压气机三者匹配良好,验证了用脉冲爆震燃烧室替代传统等压燃烧室的可行性。In order to study the detailed combustor, the turbine and the compressor, matching mechanism among the pulse detonation the pulse detonation turbine engine test system, which is mainly composed of the pulse detonation combustor, the turbocharger, the lubrication system, the engine monitoring and control system and so on, is established. The pulse detona- tion turbine engine principle experiment is carried out, and it is firstly succeed that the turbine is driven by the pulse detonation combustor and the compressor compresses air supplying for the pulse detonation combustor. The test results show that the pulse detonation turbine engine can stably work at self-suction mode durably, and the pulse detonation chamber, the turbine and the compressor match well, which verifies that using the pulse detonation combustor to alter the con- ventional isobaric combustion chamber is feasible.

关 键 词：脉冲爆震 涡轮 压气机 试验 燃烧室 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]