介质温度和工作压强对发动机燃烧室中压强振荡的影响  

Effects of Temperature and Pressure on Pressure Oscillation in the Chamber of Solid Rocket Motor

作　　者：刘佩进[1] 杨尚荣[1] 陈晓龙[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,陕西西安710072

出　　处：《推进技术》2012年第6期902-906,共5页Journal of Propulsion Technology

摘　　要：采用大涡模拟方法研究了介质温度和工作压强对模拟燃烧室中压强振荡的影响,旨在获得相同发动机结构条件下,冷流实验和发动机热试车之间压强振荡的联系,探索采用冷流实验方法研究实际发动机流动稳定性的可能性。研究结果表明对于相同结构的发动机,冷热流之间存在很大程度的一致性,全尺寸发动机的实验数据和数值模拟结果也给予了验证,介质温度决定了压强振荡的频率,工作压强决定了振荡的振幅。Large eddy simulation was used to study the effects of temperature and pressure on the oscillation in chamber, aiming to explore the pressure oscillation relationship between cold flow test and hot fire, and the possibility of using cold flow test to predict the instability of real rocket motor. The results show obvious consistency between hot and cold flow simulation at the same configuration. The experimental results of full scale motor and numerical simulation validate this consistency. The temperature dominates the oscillation frequency, and the operation pressure dominates theoscillation amplitude.

关 键 词：固体火箭发动机 压强振荡 声涡耦合 温度 压强 燃烧室 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]