通过壁温确定脉冲爆震火箭发动机中爆震波形成的位置  

Determination of Formation Position for Detonation Wave by Wall Temperature in Pulse Detonation Rocket Engine

作　　者：朱旭东[1] 范玮[1] 王可[1] 陈巍[1] 高瞻[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2012年第2期313-316,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金(50976094;51176158);教育部博士点基金项目(20096102110022);西北工业大学研究生创新实验中心资助项目(10013)

摘　　要：常用来作为促进爆震形成的Shchelkin螺旋由于流阻较大,对发动机的比冲会造成一定的损失,因此缩短缓燃向爆震转变(Deflagration to Detonation Transition,DDT)增强装置长度,对脉冲爆震火箭发动机性能的提高有着重要的意义。通过分析DDT增强段的壁温来判断爆震波的形成位置,并通过压力信号来验证。实验结果表明,DDT增强段的壁温沿轴向分布为先增加,然后保持不变,轴向温度会有一个明显的转折点;经过实验验证,壁温的转折点即为爆震波的形成位置。It would incur some loss of specific impulse resulting from the flow resistance of Shchelkin spiral which was usually used to promote detonation initiation. Thus,it is important to shorten the length of DDT section to improve the performance of PDRE. The position where detonation formed was judged by analyzing the wall temperature of the DDT section in this research, and was validated by the pressure signals. Experimental results show that the wall temperature distribution increased first and then kept constant in the axial direction. There was a obvious turning point in the axial temperature distribution. The turning point was verified as the detonation wave position.

关 键 词：脉冲爆震火箭发动机 爆震 爆震波形成位置 壁温 

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]