进口旋流方向对涡轮导叶全气膜冷却效率影响的数值研究
Numerical study on the effects of inlet swirling direction on the turbine guide vane full film cooling effectiveness
付仲议 1余强 1赵丹 1房兴龙 1黄琦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
- 折叠
摘要
为了获取旋流条件下涡轮导叶的气膜冷却特性,采用数值模拟的方法分析了逆时针和顺时针旋流对燃气涡轮一级导叶全气膜冷却效率的影响,分别总结了导叶前缘、压力面和吸力面冷却效率的变化规律.结果表明:进口旋流方向对涡轮导叶气膜冷却效率有明显影响,且不同区域的冷却效率受旋流方向的影响规律不同;叶片表面冷气受旋流影响而发生偏转.整体上看,导叶压力面的气膜冷却效率在旋流方向为逆时针条件下更高,前缘和吸力面的气膜冷却效率在旋流方向为顺时针条件下更高.
Abstract
To obtain film cooling characteristics for a turbine guide vane under inlet swirling conditions,the effects of clockwise and counterclockwise inlet swirling on the gas turbine first-stage guide vane full film cooling effectiveness were analyzed by numerical simulation.The variation rules of cooling effectiveness of the leading edge,pressure side and suction side were summarized respectively.The results show that the swirling direction of the inlet has an obvious influence on the film cooling effectiveness of the guide vane,and the cooling effectiveness in different regions is affected by the swirling direction differently.The coolant on the vane surface is deflected by swirling flow.On the whole,the film cooling effectiveness of the pressure side of the guide vane is higher when the swirling direction is counterclockwise.The film cooling effectiveness of the leading edge and suction side is higher when the direction of swirl is clockwise.
关键词
航空发动机/旋流方向/涡轮导叶/气膜冷却/冷却效率Key words
aero-engine/swirling direction/turbine guide vane/film cooling/cooling effectiveness引用本文复制引用
基金项目
中国科协青年人才托举工程()
湖南省自然科学基金(2021JJ40646)
出版年
2024
NETL
NSTL
万方数据