上游尾迹与涡轮叶栅通道涡相互作用研究  

Upstream wake-passage vortex interaction in turbine cascade

作　　者：綦蕾[1] 郑赟[1] 邹正平[1] 刘火星[1] 李维[2] 周颖[2] 许如琦[2] 

机构地区：[1]北京航空航天大学,能源与动力工程学院,航空发动机气动热力重点实验室,航空发动机数值仿真研究中心,北京100083 [2]中国航空动力机械研究所,株洲412002

出　　处：《航空动力学报》2008年第5期895-903,共9页Journal of Aerospace Power

基　　金：国家自然科学基金项目(50776003);国防基础科研项目;北京航空航天大学蓝天新星计划资助项目

摘　　要：采用三维粘性非定常数值模拟方法研究了上游尾迹与涡轮叶栅通道涡的相互作用,对定常、非定常时均以及瞬时时刻流动机理进行了分析.结果表明:上游尾迹的非定常作用一方面增强了叶栅通道涡的径向涡,使得流动损失增大;另一方面能够一定程度上抑制通道涡中流向涡的发展,对控制损失起到正面作用,端区的综合非定常效应取决于两者之间的平衡.在本文计算条件下,上述两方面综合影响使得通道涡的非定常损失增大.The internal flow of turbomachinery is intrinsically unsteady, so investigating the unsteady interactions in turbine endwall region is meaningful for improving the performance of low aspect/high loading turbine. In this paper, the upstream wake-passage vortex interactions in turbine cascade were simulated by a 3-D unsteady viscous solver, and the flow mechanisms were analyzed. Numerical results indicate that periodic upstream wakes can enhance the radial vorticity of passage vortex, which increases losses. On the other hand, upstream wakes can suppress the streamwise vorticity development of passage vortex to some extent, which reduces losses. The combined unsteady effect in the endwall region depends on the balance of above two factors. At the calculation conditions of this paper, the unsteady losses finally increased.

关 键 词：航空、航天推进系统 通道涡 上游尾迹 非定常相互作用 涡轮叶栅 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]