混合式脉冲爆震发动机原理性试验系统设计、集成与调试  

Design,integration and debugging on principle test system of hybrid pulse detonation engine

作　　者：郑龙席[1] 邓君香[1] 严传俊[1] 李娜[1] 鲍冬梅[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》2009年第1期74-78,共5页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金重点资助项目(50336030'E0604)

摘　　要：设计、集成了由涡轮增压器、脉冲爆震燃烧室、燃油供给单元、润滑单元和测控单元构成的混合式脉冲爆震发动机原理性试验系统。初步实验研究表明该系统运行可靠。当脉冲爆震燃烧室与涡轮组合工作时,可在一定频率范围内稳定工作;爆震室头部及管壁沿程压力相对于爆震室独立工作时有所提高;压气机出口空气流量远大于爆震室进口空气流量,证明利用压气机给爆震室供气是可行的。在5Hz爆震频率下,涡轮被爆震产物冲击20min后,叶片没有任何烧蚀和裂纹出现。A hybrid pulse detonation engine principle test system which is make up of turbocharger, pulse detonation combustor, fuel supply cell,lubricant cell and measuring and control cell was designed and integrated. In primary experimental research, it was found that the system can operate reliably. When pulse detonation combustor combined with a turbocharger＇ s turbine, it can operate smoothly in certain frequency range. At the head and other axial measuring locations, the peak pressure of pulse detonation combustor-turbine was higher than it was measured when the pulse detonation combustor worked separately. The air flow of turbocharger compressor exit was bigger than the air flow of pulse detonation combustor inlet. It is shown that the compressor can be used to supply sufficient air for pulse detonation combustor. At the operation frequency of 5Hz, when the turbocharger turbine had endured impact of detonation production for 20 minutes, its blades didn＇ t appear any sinter and crack.

关 键 词：混合式脉冲爆震发动机 脉冲爆震燃烧室 试验系统 设计 实验 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]