高压涡轮导叶压力面异型气膜孔特性  

Characteristics of shaped holes on the pressure surface of turbine vane

作　　者：江艳 李海旺[1,3] 谢刚[3] 陶智[1,2] 周志宇 JIANG Yan;LI Haiwang;XIE Gang;TAO Zhi;ZHOU Zhiyu(Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空发动机研究院,北京100191 [2]北京航空航天大学能源与动力工程学院,北京100191 [3]北京航空航天大学航空发动机气动热力国家级重点实验室,北京100191

出　　处：《航空动力学报》2024年第11期254-265,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(51906008,51822602);中央高校基本科研业务费(YWF-19BJ-J-293);国家科技重大专项(2017-Ⅲ-0003-0027)。

摘　　要：研究采用数值仿真方法对高压涡轮导叶压力面上圆柱孔、扇形孔、簸箕孔和后置孔的流动和传热特性进行了对比分析。其中扇形孔在展向上扩张12°,后置孔在流向上扩张7°,簸箕孔在两个方向上都有扩张。结果表明:在所研究的吹风比范围内,扇形孔和簸箕孔的气膜冷却效率最大,且当吹风比为2时,扇形孔和簸箕孔的气膜冷却效率分别最高比圆柱孔提高了128.9%和146.9%。此外,簸箕孔的热流密度净收益最大,比圆柱孔提高了28.8%,说明簸箕孔是最佳方案。另外研究发现,展向扩张角对流动和换热特性的影响大于流向扩张角,且气膜冷却效率对热流密度净收益的影响大于传热系数。Numerical simulations were employed to investigate the performance of the flow fields and heat transfer characteristics of four types of film holes:cylindrical holes,fan-shaped holes,laidback fan-shaped holes and laidback holes,on pressure surface of the turbine vane.Fan-shaped holes were expanded with the lateral divergence angle of 12 degrees compared with cylindrical holes,and laidback holes expanded with the forward divergence angle of 7 degrees.Furthermore,laidback fan-shaped holes were expanded in both directions.Results showed that fan-shaped holes and laidback fan-shaped holes showed the maximum film cooling effectiveness within the range of blowing ratios.When the blowing ratio was 2,the film cooling effectiveness of fan-shaped holes and laidback fan-shaped holes was improved to the greatest extent by 128.9%and 146.9%,respectively,in contrast with cylindrical.Additionally,laidback fan-shaped holes had the largest net heat flux reduction,28.8%higher than cylindrical holes,which indicated the laidback fan-shaped hole was the best scheme.And the forward divergence angle had less influence on the flow and heat transfer characteristics than the lateral divergence angle due to inobvious advantages of laidback holes.Besides,the effect of the film cooling effectiveness on net heat flux reduction was dominant on account of similar distributions of net heat flux reduction and the film cooling effectiveness.

关 键 词：气膜冷却 传热系数 异型孔 高压涡轮导叶 压力面 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]