超声速气流中激波对气膜冷却流动的干涉特性研究  

Interference Characteristics of Shock Wave and Film Cooling in Supersonic Flow

作　　者：高阿飞 张华良 尹钊 徐玉杰[1,2,3] 陈海生 A-fei GaoHua-liang Zhang;Zhao Yin;Yu-jie Xu;Hai-sheng Chen(Nanjing Institute of Future Energy System;Institute of Engineering Themophysics,Chinese Academy of Sciences;University of Chinese Academy of Sciences)

机构地区：[1]中科南京未来能源系统研究院 [2]中国科学院工程热物理研究所 [3]中国科学院大学

出　　处：《风机技术》2024年第3期17-24,46,共9页Chinese Journal of Turbomachinery

基　　金：国家科技重大专项(J2019-Ⅱ-0008-0028)。

摘　　要：激波会影响气膜冷却流场的流动特征,引起流场结构和冷却效率的变化。为探究激波干涉对气膜冷却的影响,本文采用数值模拟的方法对不同射流角度和不同吹风比工况下的超声速平板气膜冷却开展研究。结果表明:气膜冷却效率随吹风比的增大呈现先增大后减小的趋势,随着射流角度的增大,气膜在孔附近的展向覆盖效果逐渐提高,但冷却效率沿流向衰减加快;采用无量纲坐标系分析激波干涉对气膜流动的影响,获得激波与气膜冷却流动干涉在不同工况下对冷却效率的一致性影响规律,激波会造成冷却效率的明显降低;激波干涉下冷气容易产生三维流动分离,随着射流角度的增大,分离区极限流线的拓扑结构更加复杂。进一步引入均匀性指标参数分析激波干涉对气膜冷却效率的影响,不同射流角度下,激波干涉区域气膜冷却效率的均匀性随吹风比的增加呈先增大后减小的趋势。Shock waves can influence the characteristics of the film cooling flow field,resulting in changes to the flow field structure and cooling efficiency.In order to investigate the impact of shock interference,film cooling on supersonic flat plate varying jet angles and blowing ratios was analyzed by numerical simulation method.The results demonstrate that the film cooling efficiency exhibits an initial increase and subsequent decline with an increase in the blowing ratio.Additionally,the spreading coverage of the film near the holes gradually improves with the increase of jet angle,while the cooling efficiency is accelerated along the decay of the flow direction.To analyze the effect of shock interference on the film cooling flow,a dimensionless coordinate system is employed.It can be concluded that the shock will cause a significant reduction in the cooling efficiency.Furthermore,the coolant is prone to producing a three-dimensional flow separation under the shock interference.As the jet angle increases,the limiting streamlines topology in the separation zone becomes increasingly complex.In order to quantitatively analyze the effect of the shock interference on the film cooling efficiency,the uniformity index parameter is introduced.The uniformity of the cooling distribution in the shock interference region shows a tendency of increasing and then decreasing with the increase of the blowing ratio under different jet angles.

关 键 词：超声速 平板气膜冷却 激波干涉 气膜冷却效率 

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]