摘要
为了研究透平流道内端壁气膜冷却射流与主流二次流结构的交互作用,本文采用了RANS的数值方法,湍流模型选用SST模型,对端壁区域近吸力面典型位置处的冷气出流情况进行研究。数值分析发现,近吸力面侧出口射流在与端部涡结构的交互作用下,其冷却能力的损失反而减缓,射流能够在其下游端壁区域形成良好的冷气覆盖;在气动效率方面,射流对主流边界层的扰动使得损失的核心区增大,而横流强度则随着射流动量的增加呈现先增强后削弱的趋势。
The current study numerically analyzes the interaction mechanism between film cooling injection and main-flow secondary flow in the endwall region near suction surface using RANS with SST turbulence model.It is revealed that under the interaction between cooling injection and main-flow vortex structures near the vane suction side,the loss of the coolant cooling capacity is suppressed.Satisfactory film coverage is obtained onto the downstream endwall surface.For the aerodynamics consideration,the main-flow boundary layer is disturbed by the injection,resulting into larger area of the loss core.The intensity of the cross flow presents an up-and-down trend with increasing injection momentum.
作者
陈子聿
苏欣荣
袁新
Zi-yu Chen;Xin-rong Su;Xin Yuan(Department of Energy and Power Engineering,Tsinghua University)
出处
《风机技术》
2020年第3期46-51,共6页
Chinese Journal of Turbomachinery
基金
国家自然科学基金青年项目(No.51876098)。
关键词
气膜冷却
透平端区
二次流强度
涡系结构
横向流动
气动效率
Film Cooling
Turbine Endwall
Intensity of Secondary Flow
Vortex Structures
Cross Flow
Aerodynamic Efficiency
