大扩张比喷管分离流动冷流试验研究  

Experimental study on cold separation flow in large expansion ratio nozzle

作　　者：刘沛 李耿 赵利 

机构地区：[1]西安航天动力技术研究所,西安710025 [2]陕西宇航科技工业有限公司,西安710025

出　　处：《实验流体力学》2017年第1期62-66,共5页Journal of Experiments in Fluid Mechanics

摘　　要：为研究流动分离条件下气流特性,针对某试验大扩张比喷管,开展了地面冷流试验研究。试验得到了分离点前后测点压强与入口压强的变化规律,并对测点压强数据进行了傅里叶分析。研究结果表明,随着入口压强升高,分离点前测点压强不断升高,分离点后测点压强降低,远离分离点的下游测点压强基本不变,且略低于环境压强;流动分离会导致分离点后压强脉动增大,且脉动主要为50Hz以内的低频脉动,该研究为大扩张比喷管的设计及试验提供了重要参考。In order to investigate flow characteristics of the separation flow,cold flow tests were conducted in a solid rocket motor nozzle with a high expansion ratio under the sea level condition.The influences of the inlet pressure on the pressure of test points upstream and downstream the separation location were revealed in the tests and pressure data were analyzed by means of FFT.The results show that the pressure increases for test points upstream the separation location but decreases for test points downstream the separation location.The pressure is steady and right below the ambient pressure for test points downstream and far away from the separation location.Pressure fluctuations become more evident after separation in comparison with that before separation,and the enhanced pressure fluctuations were mainly low-frequency fluctuations in the range of 50 Hz.The research has important reference to the designing and testing of the nozzle with a high expansion ratio.

关 键 词：流动分离 冷流试验 压强脉动 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]