涡轮动叶背侧不同叶高处异型孔气膜对比  

Comparison on film cooling of different hole shapes at different blade heights on the suction surface of rotor blade

作　　者：王磊[1,3] 李海旺[2,3] 谢刚[3] 周志宇[2,3] WANG Lei;LI Haiwang;XIE Gang;ZHOU Zhiyu(School of Energy and Power Engineering,Beihang University,Beijing 102206,China;Research Institute of Aero-Engine,Beihang University,Beijing 102206,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,Beihang University,Beijing 102206,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京102206 [2]北京航空航天大学航空发动机研究院,北京102206 [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,北京102206

出　　处：《航空动力学报》2024年第5期62-70,共9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：采用数值仿真的方法对比研究了涡轮转子叶片背侧不同叶高位置处的圆柱孔、扇形孔和簸箕孔三种孔型气膜冷却的差异。气膜孔位于吸力面17.8%流向位置,并分别在10%、30%、50%、70%和90%叶高位置各设有一个气膜孔,三种孔型的圆孔段直径均为0.8 mm。研究在600 r/min转速(对应旋转雷诺数为536 000)条件下开展并获得吹风比为0.50、0.75、1.00、1.25和1.50条件下的气膜冷却效率分布。研究结果指出:不同叶高位置处的气膜尾迹受叶根通道涡和叶顶泄漏流的影响呈现不同程度地向中间叶高位置偏转的趋势,因此不同叶高位置处的气膜尾迹内的涡对结构不对称的特征也不同。随着吹风比的增加,出现最大气膜冷却效率的叶高位置逐渐向叶顶方向移动。使用扇形孔和簸箕孔可以削弱冷却射流在气膜孔出口位置的法向动量,提升了气膜的附壁性和气膜冷却效率。Simulations were performed to study the downstream film cooling performance of round holes,fan-shaped holes,and laid-back fan-shaped holes at different heights on the suction surface of a rotor blade.Film holes were located at streamwise location of 17.8%and at 10%,30%,50%,70%and 90%blade heights,respectively.The diameter of the round section of each shaped hole was 0.8 mm.Studies were conducted at rotational speed of 600 r/min,corresponding to rotational Reynolds numbers of 536000.Five blowing ratios of 0.50,0.75,1.00,1.25 and 1.50 were involved.Results showed that under the effects of passage vortex and tip leakage flow,inward film deflection trend towards the mid-span on the suction surface differed at different blade heights,corresponding to different degrees of structural asymmetry of counter rotating vortex inside film trajectories at different blade heights.With the increase of blowing ratio,the height at which the highest film cooling effectiveness appeared gradually moved upward. The introduction of fan-shaped hole and laid-back fan-shaped hole weakened the normalmomentum of the jet at the hole exit and improved film coverage and film cooling effectiveness.

关 键 词：气膜冷却 涡轮动叶 吸力面 叶高位置 异型孔 吹风比 

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]