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高温燃气流风洞试验舱压的影响因素研究
王彪1,曹知红1,姜一通1,田宁1,赵玲1,2
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
摘要:
针对高温燃气流风洞实际试验过程中舱压变化的情况,选取了收集口位置、收集器豁口、主动控制和堵塞比四种不同的影响因素,使用试验和三维CFD(Computational Fluid Dynamics)方法对舱压试验匹配性的影响进行了相关的研究。数值研究与试验结果的趋势一致,舱压都随着影响因素数值的增加而升高。依据对舱压的影响程度的差异,这四种因素由大到小依次为堵塞比、主动控制、收集口位置和收集器豁口,计算范围内对舱压变化的最大影响程度分别为345%,271%,139%和18%。这些因素都破坏了溢流与主流引射之间的初始平衡,通过或相当于增加向试验舱内的溢流和减小主流的引射能力来提高舱压。
关键词:  高温风洞  舱压  收集口  主动控制  阻塞比
DOI:10.13675/j.cnki.tjjs.2211076
分类号:V211.21
基金项目:
Influencing factors of test cabin pressure for high temperature gas flow wind tunnel
WANG Biao1, CAO Zhihong1, JIANG Yitong1, TIAN Ning1, ZHAO Ling1,2
1.Beijing Institute of Space Long March Vehicle,Beijing 100076,China;2.Institute of Aero Engine,Tsinghua University,Beijing 100084,China
Abstract:
Based on the changes of cabin pressure in the actual experiment for the high temperature gas flow wind tunnel, four influence factors, namely collector position, collector opening, active control and blockage ratio, were selected to be studied. Three-dimension computational fluid dynamics (CFD) method and experiments were used to carry out the relevant research about the influence of these factors on experimental matching of cabin pressure. The numerical results are consistent with the experiment. The cabin pressure increases with the value increase of influence factor. According to the degree of influence on cabin pressure, the decreasing orders of these four factors are blockage ratio, active control, collector position and collector opening. The maximum influence degrees within the computational range are 345%, 271%, 139% and 18%, respectively. These factors all destroy the initial balance between overflow and mainstream ejection. They all increase the cabin pressure through increasing the overflow to test cabin and reducing the ability of mainstream ejection.
Key words:  High temperature wind tunnel  Cabin pressure  Collector port  Active control  Blockage ratio