Mechanism of compressor airfoil boundary layer flow control using nanosecond plasma actuation

被引：19

作者：

Zhang Haideng ^{[1
,2
]}

Wu Yun ^{[1
,2
]}

Li Yinghong ^{[1
]}

机构：

[1] Airforce Engn Univ, Key Lab Plasma Dynam, Xian 710038, Shaanxi, Peoples R China

[2] Xi An Jiao Tong Univ, Sch Mech Engn, Xian 710049, Shaanxi, Peoples R China

来源：

INTERNATIONAL JOURNAL OF HEAT AND FLUID FLOW | 2019年 / 80卷

基金：

中国国家自然科学基金;

关键词：

Compressor airfoil; boundary layer; flow control; nanosecond plasma actuation; CONTROLLED DIFFUSION AIRFOILS;

D O I：

10.1016/j.ijheatfluidflow.2019.108502

中图分类号：

O414.1 [热力学];

学科分类号：

摘要：

The flow control effects of nanosecond plasma actuation on the boundary layer flow of a typical compressor controlled diffusion airfoil are investigated using large eddy simulation method. Three types of plasma actuation are designed to control the boundary layer flow, and two mechanisms of compressor airfoil boundary layer flow control using nanosecond plasma actuation have been found. The plasma actuations located within the laminar boundary layer flow can induce a small vortex structure through influencing on the density and pressure of the flow field. As the small vortex structure moves downstream along the blade surface with the main flow, it can suppress the turbulent flow mixing and reduce the total pressure loss. The flow control effect of the small vortex structure is summarized as wall jet effect. Differently, the plasma actuation located within the turbulent boundary layer flow can act on the shear layer flow and induce a large vortex structure. While moving downstream, this large vortex structure can suppress the turbulent flow mixing too.

引用

页数：10

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