吸力面等离子体激励对低压涡轮叶栅流场的影响研究  

The Effect of Suction Side Plasma Actuation in the Low-Pressure Turbine Cascade

作　　者：赵旭 王云飞 马晓钟 张耀文 岳隆 ZHAO Xu;WANG Yunfei;MA Xiaozhong;ZHANG Yaowen;YUE Long(School of Transportation and Vehicle Engineering,Shandong University of Technology,Zibo 255000,China)

机构地区：[1]山东理工大学交通与车辆工程学院,淄博255000

出　　处：《真空科学与技术学报》2023年第12期1072-1080,共9页Chinese Journal of Vacuum Science and Technology

基　　金：山东省自然科学基金青年项目(ZR2020QE190)。

摘　　要：为探究等离子体激励对尾迹扫掠下低压涡轮叶栅吸力面附面层分离和总压损失的控制机理,文章采用数值模拟方法分析等离子体激励效应对叶栅流场的作用规律,探究激励位置对流动控制效果的影响。研究表明,激励位置从时均分离点上游向尾缘移动时,叶栅出口处总压损失系数呈现先减小后增大的趋势。当激励器处于吸力面时均分离点下游5%轴向弦长位置,吸力面后部附面层分离现象完全被抑制,出口总压损失系数下降约10%。在吸力面后部施加激励能有效抑制吸力面上的附面层分离,但对端壁区的流场影响较小。To investigate the control mechanism of plasma actuation on the boundary layer separation and the total pressure loss of the low-pressure turbine cascade with incoming wakes,a numerical simulation is conducted to analyze the effect of plasma actuation on the flow field.The influence of the actuation position on flow control effectiveness is explored in detail.As the actuation position moves from upstream of the time-averaged separation point to the trailing edge,the total pressure loss coefficient at the outlet exhibited a trend of initially decreasing and then increasing.When the actuator is located 5%axial chord length downstream of the time-averaged separation point,the boundary layer separation at the rear part of the suction surface is completely suppressed,and the total pressure loss coefficient at the outlet decreases by approximately 10%.Plasma actuation applied at the rear of the suction surface can effectively suppress boundary layer separation on the suction surface while having little effect on the flow field in the end wall area.

关 键 词：低压涡轮 流动控制 等离子体激励 附面层分离 总压损失 

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]