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论文类型：期刊论文

发表时间：2018-02-01

发表刊物：PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING

收录刊物：SCIE、EI

卷号：232

期号：2

页面范围：374-387

ISSN号：0954-4100

关键字：Dimpled surface; highly loaded compressor cascade; flow control; topological structure; numerical simulation

摘要：This study investigates the influence of geometry parameters of dimples on the blade surface in a high-turning linear compressor cascade. Four arrays of dimples with a depth-to-diameter ratio of 0.25 and the depth varying from 0.1mm to 0.6mm in six different configurations were erected to explore their effects on loss coefficients, streamline patterns, topology structure as well as vortex structure. The dimple configurations were evenly distributed among 42-65% axial chord on the suction surface. The Reynolds-averaged Navier-Stokes method was used in the computational investigation under the nominal condition. The results show that the dimples with proper size can positively affect the flow loss and flow pattern. The larger dimples do not dramatically overtake the smaller ones in loss reduction, suggesting that there exists an optimal size of dimples in loss reduction within compressor cascades. The total number of singular points and separation lines in the cascade are both reduced under the dimple configurations. Furthermore, the vortex structures of the prototype and a prominent dimple configuration were depicted in detail. Passage vortex plays a dominant role in organizing the fluid within the cascade. The dimple configurations can suppress the migration of passage vortex along the spanwise direction and thereby decreases its influence region.