叶顶间隙影响高负荷扩压叶栅气动性能实验研究  

An Experimental Investigation on the Aerodynamic Performance of Highly-loaded Compressor Cascade with Different Tip Clearance

作　　者：陆华伟[1] 杨益[1] 刘俊[1] 郭爽[2] 王安妮[1] 韩兴伟[1] 钟兢军[1] 

机构地区：[1]大连海事大学轮机工程学院,大连116026 [2]大连理工大学航空航天学院,大连116024

出　　处：《工程热物理学报》2017年第3期509-514,共6页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51676023;No.51506022;No.51436002);辽宁省自然科学基金项目(No.201602078);中央高校基本科研业务费专项资金(No.DUT16K08)

摘　　要：针对高负荷扩压叶栅,实验测试了叶顶间隙尺寸变化对叶栅气动特性的影响规律。结果表明,在马赫数和冲角固定时,随着间隙尺寸的增加,由于间隙泄漏流动与横向压力梯度的相互作用,近端壁附面层低能流体的聚集和发展受到影响,叶栅损失呈现先减小后增大的趋势,存在最佳间隙尺寸使得损失最小。本文研究的高负荷扩压叶栅中实验测的最佳间隙为1%相对叶高。In this paper,an experimental investigation was conducted to validate the effect of magnitude of tip clearance on the aerodynamic performance for a highly-loaded compressor cascade.The experimental results show that,under the specific Mach number and incidence angle,the loss of cascade exhibits the tendency of increasing after an initial decreasing with the increase of tip clearance magnitude.The reason for this phenomenon is considered to have relationship with the accumulation and expansion of low-energy fluid in boundary layer,affecting by the interaction of tip leakage flow and cross pressure gradient.The best magnitude of tip clearance which represents the minimal loss was validated as 1%of relative span for a highly-loaded compressor cascade experimentally.

关 键 词：高负荷扩压叶栅 叶顶间隙 泄漏流动 气动性能 实验研究 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]