吸力面附面层抽吸对大转角扩压叶栅气动性能影响  

Effects of Boundary Layer Suction on the High-turning Compressor Cascade

作　　者：陆华伟[1] 张永超[1] 康达[1] 阚晓旭[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《节能技术》2015年第2期131-135,139,共6页Energy Conservation Technology

基　　金：国家自然科学基金资助项目(51206013);高等学校博士学科点项目科研基金(20112125120009);中央高校基本科研业务费专项资金(3132014049)

摘　　要：为研究附面层抽吸对大转角扩压叶栅气动性能的影响,借助实验校核CFD方法,探究了沿叶片弦向吸力面不同抽吸位置及抽吸流量对损失的抑制效应。结果表明附面层抽吸技术可以很好的控制叶型损失,改善角区流动形态,吸力面最佳抽吸位置位于分离线起始位置处,且在小抽吸流量范围内,随抽吸流量的增大损失逐步降低,但降低幅度逐渐减少。The CFD that was verified by an experiment was conducted to study the loss of highly-loaded compressor cascade. The effects of boundary layer suction on flow properties were investigated as well.The inhibitory effect on loss was explored in different suction location and mass flow. Results show that the blade losses were well controlled through boundary layer suction and the flow status was improved in the meantime. The optimum slot is located in the beginning of separation line in suction side,and losses decrease gradually with the increase of mass flow while the decrease range reduces under the low suction mass flow.

关 键 词：附面层 分离 抽吸 流量 损失 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]