弯曲壁面冲击加发散冷却结构的冷却效果实验研究  

Experimental Investigation on Cooling Performance of Impingement/Effusion Cooling Structures on Concave Wall

作　　者：石小祥 胡好生[1] 杨卫华[2] 王梅娟[1] SFII Xiao-xiang HU Hao-sheng YANG Wei-hua WANG Mei-juan(China Aviation Powerplant Research Institute, AVIC, Zhuzhon 412002, China College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)

机构地区：[1]中国航空工业集团中国航空动力机械研究所,湖南株洲412002 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2017年第3期630-636,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(51276088)

摘　　要：为了研究双层壁压降分配对弯曲壁面冲击加发散冷却效果的影响,针对回流燃烧室大弯管双层壁冷却结构,保证相同当量开孔率通过调整冲击孔壁和发散孔壁的有效开孔面积之比得到了不同压降分配的冷却方案,并提出了一种六边形排布方式,选取4种冷却结构进行了冷却效果实验研究。研究表明:在相同的冷热侧进气条件下,冲击孔壁压降分配比例由19%增加至71%时,常规菱形排布结构的平均冷却效率可以提高29%,而六边形排布结构的平均冷却效率可以提高36%以上;另外,加温比对冷却效率影响较小。In order to study the effects of pressure drop distribution on impingement/effusion cooling performance in the transition section of reverse flow combustor,different cooling structures with various pressure drop distribution but same equivalent orifice area were designed through adjusting the effective orifice area ratio of impingement wall to effusion wall.In addition,a novel hexagonal holes arrangement was put forward.Experimental investigation on the cooling effectiveness of four specific double-wall cooling structures was conducted under the same condition of cooling air and main flow.The results show that the higher pressure drop distribution ratio results in an extreme enhancement of cooling performance, the average cooling effectiveness of the structures punched in rhombus arrangement and hexagonal arrangement is improved by 29% and 36%, respectively,while the pressure drop distribution ratio increases from 19% to 71%.Furthermore,the temperature ratio of main flow to cooling air shows limited effect on cooling effectiveness under the condition of same mass flow flux.

关 键 词：回流燃烧室 弯曲壁面 冲击加发散冷却 压降分配 冷却效率 六边形排布 

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]