吸附式跨声速压气机叶栅流场数值模拟

Numerical investigation of boundary layer suction in an axial transonic compressor cascade

1.
Institute of Engineering Thermophysics, Chinese Academy of Science, Beijing 100080, China
2.
Shenyang Aeroengine Research Institute, Shenyang 110015, China

摘要: 使用MISES程序数值模拟了跨声速吸附式压气机叶栅流场, 重点研究了吸气量和吸气位置对跨声速压气机叶栅气动性能的影响.结果表明, 叶栅来流马赫数和方向一定时, 吸气位置和吸气量是相互关联的关键参数, 不同的吸气位置对应着不同的最佳吸气量, 且随着吸气位置向后缘远离激波, 最佳吸气量呈逐渐增大之势.从吸气对叶片吸力面边界层的影响效果分析, 理想的吸气位置应该是在靠近激波后附面层发展到一局部极大值即将进入过渡段的位置附近.
- 航空、航天推进系统 /
- 跨声速 /
- 吸附式 /
- 吸气量 /
- 吸气位置 /
- 叶栅
Abstract: Based on the numerical investigations on the performance of an axial transonic compressor cascade with different suction slot locations and suction mass-flow, it has been shown that for a given inlet Mach number and flow angle, there exist an optimal suction mass-flow corresponding to the suction slot location.And the optimal suction mass-flow increases as the suction slot moves far from the shock location towards the trailing edge.The perfect suction slot location should be at the beginning of the transition region where the boundary layer thickness has developed to a local maximum value downstream of the shock.
- aerospace propulsion system /
- transonic /
- suction /
- suction mass-flow coefficient /
- suction slot location /
- cascade

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