跨声速叶栅叶表附面层抽吸效应试验  

Experimental investigation of boundary layer suction effects on a transonic cascade

作　　者：王掩刚[1,2] 国睿[1] 任思源[1] 姜正礼[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空工业集团公司中国燃气涡轮研究院,成都610500

出　　处：《航空动力学报》2011年第9期2068-2074,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50806061);西北工业大学翱翔之星计划

摘　　要：以某跨声速、吸附式叶栅为研究对象,在暂冲式叶栅风洞上对其进行了多个状态的吹风试验,对比分析了在通道存在激波条件下,激波前、后抽吸对叶栅性能以及附面层的影响效应.研究结果表明:激波前抽吸使得抽吸缝局部马赫数增大,恶化叶栅性能;激波前抽吸对于来流高亚声和超声速的叶栅损失系数影响趋势一致,随着抽吸系数增加损失系数增加,并且当抽吸系数大于0.2%时,损失系数增加较快;波后抽吸可明显改善叶栅性能,抽吸量越大,抽吸正效应越明显,相比于未抽吸条件,抽吸系数为0.8%时损失系数降低8%、总压恢复系数提高5%.To explore the effects of boundary layer suction（BLS） on a transonic cascade,several experiments were carried out on an intermittent cascade wind tunnel.The results of different locations in relation to the point for passage shock wave projection of various suction coefficients have been investigated.Experimental results show that：when the location of BLS slot is in front of the point for passage shock wave projection,the local Mach number around the suction slot is increased and cascade performance is deteriorated.The loss coefficient increases with the enhancement of suction coefficient for both higher subsonic and supersonic inlet flow conditions,and when the suction coefficient is greater than 0.2%,the loss coefficient increases rapidly.When BLS slot is located behind the shock wave,the cascade performance is significantly improved,and the positive effect of BLS increases by the suction coefficient.Compared with the condition without suction,the loss coefficient reduces by 8% and the total pressure recovery coefficient increases by 5% when suction coefficient is 0.8%.

关 键 词：跨声速叶栅 激波 附面层 抽吸流 损失系数 

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]