栅前端壁射流抑制二次流的数值研究  

Numerical Study on Suppression of the Secondary Flow by Endwall Jet in Leading Edge

作　　者：赵树 陈榴[1] 戴韧[1] ZHAO Shu;CHEN Liu;DAI Ren(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai 200093,China)

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《动力工程学报》2021年第5期380-386,共7页Journal of Chinese Society of Power Engineering

基　　金：国家自然科学基金资助项目(52006147)。

摘　　要：基于射流的主动流动控制方法,在透平叶栅端壁前缘位置开设射流孔。通过数值模拟分析了射流孔位置、倾斜角、俯仰角和动量系数等因素对前缘马蹄涡以及流动损失的影响。结果表明:在前缘马蹄涡流动分离线上布置射流孔以及倾斜角方向与射流孔所在位置的近端壁极限流线保持一致的情况下,射流孔俯仰角为40°、动量系数为0.1%时总压损失系数比达到最小,将其作为最优组合方案;该方案可以抑制前缘马蹄涡的多涡系结构,并削弱其湍动能,降低流动损失,近出口处总压损失系数可降低8.83%。Based on the active flow control method of jet flow, jet holes were set at the leading edge of turbine cascade endwall.Effects of jet hole position, skew angle, pitch angle and momentum coefficient on leading edge horseshoe vortex and flow loss were analyzed by numerical simulation.Results show that as the jet holes are arranged on the separation line of leading edge horseshoe vortex flow and the skew angle direction is consistent with the limit streamline of the proximal endwall where the jet holes are located, the ratio of total pressure loss coefficient reaches the minimum in the case of pitch angle β=40° and momentum coefficient Cμ=0.1%, which is regarded as the optimal combination scheme.The scheme can suppress the multi-vortex structure of the leading horseshoe vortex, weaken the strength of turbulent kinetic energy and reduce the flow loss. Finally, the total pressure loss coefficient near the outlet can be reduced by 8.83%.

关 键 词：射流 二次流 透平叶栅 马蹄涡 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程]