摘要
在单级轴流压气机上,用周向槽式处理机匣在静子内径处进行轮毂处理,与转子尖部机匣处理作类比。用小型5孔探针测试技术详细测量了在最佳工作状态和近失速边界状态下静子叶片排下游气流的三元流场,特别是其端部流场,发现对于转子叶尖失速型的级,在其静子轮毂处理也可以提高级的稳定裕度。并提出其扩稳机理与失速转移的关系,提出了周向诱导速度影响二次流的物理模型,进一步剖析了周向槽机匣处理的扩稳机理。
The hub treatment with a circumferential groove was tested on the stator hub and compared with the casing treatment over the rotor tip for a single stage axial flow compressor. The 3D flowfield at the downflow of stator blade rows, particularly its endwall flowfield in optimum operation and near stall state were measured by a microfive-hole probe. It was shown that stall margin can be improved , even if the onset of stall is at the rotor tip first. The relation between the mechanism of stability extension and stall transfer was obtained. A physical modle of effect of circumferential inducing velocity on the endwall secondary flow is proposed. The mechanism to extend stability of circumferential grooved hub treatment was also analyesd with more details.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第8期B370-B373,共4页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金
关键词
机匣处理
不稳定流动
压气机
casing treatment, unsteady flow, compressor
