涡轮叶片全表面换热特性的试验与数值研究
Experimental and numerical investigation of heat transfer characteristics on the whole turbine vane surface
薛树林 1吴学深 2吴楠 1刘丽平 1郝旭生 1余毅1
作者信息
- 1. 中国航发湖南动力机械研究所,湖南 株洲 412002;中小型航空发动机叶轮机械湖南省重点实验室,湖南 株洲 412002
- 2. 陆装航空军代局驻株洲地区航空军代室,湖南 株洲 412002
- 折叠
摘要
通过试验与数值计算相结合的方法,对无气膜涡轮叶片和带叶盆、叶背两排气膜孔涡轮叶片的全表面的换热进行了对比研究.结果表明,叶片表面换热特性受叶栅通道结构影响较大,在叶片前缘驻点和叶栅通道喉部主流加速剧烈位置流动换热程度较高,通道涡的产生明显增强了叶片端部换热效果且使气流向叶片中部收缩;气膜孔可明显增强叶片表面局部对流换热特性,但对叶片全表面换热趋势影响不大.
Abstract
A comparative study on heat transfer characteristics of the whole turbine vane surface without films and another one with two rows of film holes was conducted through tests and numerical calculations.The results show that the heat transfer of the vane surface is influenced greatly by the cascade passage structure.Heat transfer is strong at the stagnation point of the vane leading edge and the mainstream severely accelerated position.The generations of channel vortices enhance the heat transfer at the vane end wall and compress the mainstream towards the middle of the vane.Film holes can enhance local convection heat transfer of the vane surface,but do not change the trend of the whole vane surface heat transfer.
关键词
航空发动机/涡轮叶片/对流换热/气膜冷却/试验/数值模拟Key words
aero-engine/turbine vane/convective heat transfer/film cooling/experiment/numerical simulation引用本文复制引用
出版年
2024
NETL
NSTL
万方数据