凹腔支板尾缘涡脱落频率试验研究  

Experimental Study of Vortex Shedding Frequency at Trailing Edge of a Cavity-Based Strut

作　　者：吴迪[1] 金捷[1] 季鹤鸣[2] 徐胜金[3] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中航工业沈阳发动机设计研究所,沈阳110015 [3]清华大学航天航空学院,北京100084

出　　处：《航空发动机》2011年第4期48-50,4,共4页Aeroengine

摘　　要：为研究不同结构尺寸的凹腔对支板尾缘涡脱落频率特性的影响,设计了用于一体化加力燃烧室的带凹腔支板部件,并对其进行了风洞冷态试验。对所测得的速度数据进行频谱分析,并与标准支板的相关数据进行对比。结果表明:开凹腔设计改变了涡脱落频率变化趋势,而不同结构尺寸的凹腔对尾迹区涡脱落频率的影响相近。In order to study the effect of different cavities on the vortex shedding frequency at the railing edge of a strut, a series of cavity-based struts used for the integrated afterburner were designed. The wind-tunnel cold tests were carried out for those struts. The spectrum analysis of the speed data obtained from the tests were completed, and compared with the data about the standard struts. The results show that the variation trend of the vortex shedding frequency are altered by various cavities, but the effects of variuus cavities on the its trailing edge vortex shedding frequency are similar.

关 键 词：支板 凹腔 频率 加力燃烧室 航空发动机 试验 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]