小弯管冲击冷却结构流场和温度场的场协同分析  

Field Synergy Between Flow Field and Temperature Field in Concave Wall Impingement Cooling Structure

作　　者：赵鸿华 宋双文 王志凯 姜世界 ZHAO Hong-hua;SONG Shuang-wen;WANG Zhi-kai;JIANG Shi-jie(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Research Institute of Aero-Engine,Beihang University,Beijing 100191,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]北京航空航天大学航空发动机研究院,北京100191

出　　处：《推进技术》2023年第4期124-130,共7页Journal of Propulsion Technology

摘　　要：为研究回流燃烧室小弯管冲击冷却结构能量传递过程中对流换热的物理机制,基于场协同理论,对冲击孔径di、冲击孔流向间距S、冲击孔展向间距P耦合作用及冲击孔倾角α1对小弯管冲击冷却结构换热特性的影响开展了场协同分析,并对场协同分析结果进行了试验验证。研究结果表明:协同角较小的区域主要分布在冲击腔内的流动滞止区、壁面射流区和滞止点,换热效果较好;随着S/P增大,冲击腔内平均协同角先减小后增大,在S/P为0.8时,换热效果最佳;随着S/di和P/di增大,冲击腔内平均协同角增大,换热效果减弱;随着α1增大,冲击腔内平均协同角先增大后减小,在冲击孔垂直壁面时换热效果最佳。In order to study the physical mechanism of convective heat transfer in the process of energy transfer in the impingement cooling structure of concave wall in reverse flow combustor,based on the field synergy theory,the influences of the coupling effects of the impingement hole diameter di,the impingement hole flow spacing S,the impingement hole spanwise spacing P and the impingement hole inclinationα1 on the heat transfer characteristics of the impingement cooling structure of concave wall were analyzed,and the results of the field synergy analysis were verified by experiments.The results show that the regions with small synergy angle are mainly distributed in the flow stagnation zone,wall jet zone and stagnation point in the impingement chamber,and the heat transfer effect is good.With the increase of S/P,the average synergy angle in the impingement chamber decreases first and then increases,and the heat transfer effect is the best when S/P is 0.8.With the increase of S/di and P/di,the average synergy angle in the impingement chamber increases,and the heat transfer effect weakens.With the increase ofα1,the average synergy angle increases first and then decreases,and the heat transfer effect is the best when the impingement hole is perpendicular to the wall.

关 键 词：回流燃烧室 小弯管 冲击冷却 场协同理论 换热特性 

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]