摘要
在低速平面叶栅风洞中,对不同间隙大小条件下的高负荷压气机叶栅流动特性进行了实验研究。实验采用五孔气动探针测量了叶栅出口截面参数,得到了该截面的二次流速度矢量分布,并对叶栅下端壁和叶片表面进行了墨迹流动显示.结果表明,叶顶间隙的增加加剧了间隙泄漏流动与通道涡的相互作用和掺混,导致叶栅流道内的二次流结构和形态发生改变;增加叶顶间隙可完全抑制吸力面角区分离,但被间隙泄漏流动带走的低能流体被带到尾缘及其下游位置,加剧了相应位置的流动分离;间隙泄漏流动将引起叶栅总损失的显著下降,损失的大小并不一定与间隙大小成正比.
The flow characteristic of highly-loaded compressor cascade in different gap height condi- tions were investigated experimentally in a low-speed plane cascade wind tunnel. The distributions of the exit secondary flow vector and the exit aerodynamic parameters were measured by five-hole probe in detail. Also, the ink-trace flow visualizations on the cascade surface and lower endwall were performed. The results show that the increase in tip clearance exacerbated the Interaction and blending between leakage flow passage and vortex. Thus, the structure and shape of the secondary flow in the flow channel between the cascades changed; The increase in tip clearance could completely inhibited the corner separation from suction surface. Low energy fluid which was taken away by clearance leakage flow was brought to the trailing edge and its downstream position. The above condition exacerbated flow separation in some corresponding situations; Leakage flow will cause a significant reduction for the total loss of the cascade. The extent of the loss is not necessarily proportional to the gap height.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2014年第1期34-37,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No.51206035)
国家自然科学基金创新研究群体项目(No.51121004)
中央高校基本科研业务费专项基金(No.HIT.NSRIF.2010033)资助
关键词
航空
航天推进系统
压气机叶栅
间隙
流动特性
实验研究
aviation, aerospace propulsion system
compressor blade
clearance
flow characteristic
experimental study
