高温风洞收集口对舱压试验匹配性影响的研究  

Influence of the Collector on the Experimental Matching of Chamber Pressure in High Temperature Gas Flow Wind Tunnel

作　　者：王彪 曹知红 李彦良 田宁[1] 赵玲 WANG Biao;CAO Zhihong;LI Yanliang;TIAN Ning;ZHAO Ling(Beijing Institute of Space Long March Vehicle,Beijing,100076;Institute of Aero Engine,Tsinghua University,Beijing,100084)

机构地区：[1]北京航天长征飞行器研究所,北京100076 [2]清华大学航空发动机研究院,北京100084

出　　处：《导弹与航天运载技术（中英文）》2024年第2期80-85,共6页Missiles and Space Vehicles

摘　　要：针对高温燃气流风洞试验中舱压不稳定可能造成试验设施损害的问题,从波系与分离涡之间相互干扰的角度,开展了扩压器的收集口位置和尺寸对舱压试验匹配性影响的机理研究。使用计算流体力学方法对不同收集口位置和尺寸的工况进行了模拟,得到了试验舱内的压力分布情况,研究了波系与分离涡之间的相互干扰对试验稳定运行的影响,为收集口的优化设计提供了参考。研究表明,合理的收集口位置和尺寸,能够增强波系与锥身后的分离涡的相互影响,避免分离涡主导收集口,增加主流的通流量,减小舱内溢流及其产生的回流涡的尺度,有利于试验的成功开展。Aiming at the damage problem of experimental facilities caused by unsteady chamber pressure in experiment of high temperature gas flow wind tunnel,the mechanism of the influence of collector positions and dimensions on the stability of experimental flow field is studied.Study mainly focuses on the interaction between the waves and separated vortexes.Utilizing CFD method,the pressure distribution is obtained in the chamber.Then the relationship between the interaction of the waves and separated vortexes and experimental stability are also explored,which will provide a reference for the optimal design of the collector.The results show that appropriate collector position and reasonable collector dimensions can reduce the overflow in the chamber.It can also avoid the separated vortex dominating the collector port,and increase the flow of mainstream.It is helpful to the conduction of experiment.

关 键 词：高温燃气流风洞 扩压器 收集口 舱压 波涡相互干扰 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]