动静干涉下高压涡轮外环非定常气膜冷却性能分析  

Unsteady Film Cooling Performance Analysis of High-pressure Turbine Shroud under Rotor-stator Interaction

作　　者：寇志海 丛培根 韩博 李广超 尹训彦 KOU Zhi-hai;CONG Pei-gen;HAN Bo;LI Guang-chao;YIN Xun-yan(School of Aero-engine,Shenyang Aerospace University,Shenyang 110136)

机构地区：[1]沈阳航空航天大学航空发动机学院,沈阳110136

出　　处：《航空发动机》2023年第4期9-15,共7页Aeroengine

基　　金：国家自然科学基金(51406124);辽宁省教育厅科研项目(JYT19060)资助。

摘　　要：为了探索航空发动机高压涡轮外环非定常气膜冷却性能的影响因素及其作用规律,对叶片高速旋转作用下某航空发动机高压涡轮外环的非定常气膜冷却过程进行了3维数值模拟。应用滑移网格技术实现了涡轮叶片与涡轮外环壁面之间的相对运动以及转子与静子之间干涉作用的模拟;分析了叶片的旋转作用、吹风比、气膜射流方向、气膜轴向射流角度等因素对高压涡轮外环非定常气膜冷却性能的影响规律。结果表明:在高吹风比下应防止叶片前缘上游气膜孔冷却裕度不足现象的发生;逆向排布的气膜孔更适合在高吹风比下使用;当气膜入射角由45°减小为30°时,外环面平均气膜冷却效率时均值增大18.54%,显著提高了涡轮外环冷却的冷气利用效率。In order to explore the influence law of unsteady film cooling performance of the high-pressure turbine shroud,the threedimensional numerical simulation was carried out to investigate the unsteady film cooling of the high pressure turbine shroud for an aeroengine under high speed blade rotation.The rotor-stator interaction and the relative motion between the turbine blade and the turbine shroud were realized by the sliding grid technique.Effects of the turbine blade rotation,the blowing ratio,the film injection direction and the film injection angles on the film cooling efficiency of the turbine shroud were analyzed.It is found that the lack of cooling ability for the first-row film hole in the high blower ratio should be prevented.It is more favorable for improvement on the film cooling performance of the turbine shroud in the high blower ratio to apply the reverse arrangement of film holes.When the incidence angle of the cooling gas decreas⁃es from 45°to 30°,the mean average film cooling efficiency of the turbine shroud increases by 18.54%,which significantly improves the utilization efficiency of cooling gas.

关 键 词：高压涡轮外环 非定常气膜冷却 叶顶间隙 泄漏流 泄漏涡 动静干涉 航空发动机 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]