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首页> 外文期刊>Aerospace science and technology >Control of corner separation via dimpled surface for a highly loaded compressor cascade under different inlet Mach number
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Control of corner separation via dimpled surface for a highly loaded compressor cascade under different inlet Mach number

机译：在不同的进气马赫数下，通过起皱表面控制高负载压缩机叶栅的转角分离

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摘要

In this paper, flow characteristics of dimpled compressor cascades are numerically discerned by solving the compressible Reynolds-averaged Navier-Stokes equations on structured grids over the inlet Mach number ranging from 0.3 to 0.8. Four rows of parallel, spherical dimples with a depth of 0.2 mm and a depth-to-diameter ratio of 0.25 are embedded along 10%-32% and 38%-60% chord of suction surface respectively. Results showed that two dimple configurations can both reduce the total pressure loss in all researched Mach number except that of 0.8. The suppression of three-dimensional separation near the hub-corner region is the primary cause of loss reduction. What's more, the separation bubble on the suction surface can be also eliminated or depressed due to the disturbance and higher level of turbulence kinetic energy within boundary layer. According to the distribution of axial vorticity in flow passage, the dimpled vortex can also suppress the migration of secondary flow along spanwise direction under a relative higher cross pressure gradient. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：在本文中，通过求解入口马赫数在0.3到0.8范围内的结构化网格上的可压缩雷诺平均Navier-Stokes方程，可以从数值上识别出凹窝式压缩机叶栅的流动特性。沿吸力面弦的10％-32％和38％-60％分别埋入四排平行的球形凹坑，深度为0.2 mm，深径比为0.25。结果表明，除了0.8以外，在所有研究的马赫数中，两种酒窝配置均可降低总压力损失。抑制中心角区域附近的三维分离是减少损耗的主要原因。此外，由于边界层内的扰动和更高水平的湍流动能，也可以消除或抑制吸入表面上的分离气泡。根据流动通道中轴向涡度的分布，凹坑涡流还可以在相对较高的交叉压力梯度下抑制二次流沿展向方向的迁移。 （C）2018 Elsevier Masson SAS。版权所有。

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