回流燃烧室弯曲段冲击扰流柱+逆向对流+气膜冷却效率  

Cooling Effectiveness of Impingement Pin-Fin+Reversed Convection+Film in Curved Section of Combustion Chamber

作　　者：曹俊[1] 熊纯[2] 杨卫华[3] 宋双文[1] 

机构地区：[1]中国航空动力机械研究所,株洲412002 [2]长沙航空职业技术学院,长沙410124 [3]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2011年第2期178-183,共6页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：南京航空航天大学基本科研业务费专项科研(NS2010053)资助项目

摘　　要：为从理论上分析研究回流燃烧室弯曲段冲击扰流柱+逆向对流+气膜冷却结构的传热特性,设计了多种不同几何尺寸的计算模型,运用F luen t软件从流动与换热两个方面对其进行了系统的研究,得出了如下结论:(1)扰流柱的存在强化了冷却空气在冲击腔中的扰动,使得冷却空气与冷侧壁面的换热得到大大地加强,提高了复合冷却结构的冷却效率;(2)在本文研究的几何尺度下,附着于弯曲段热侧壁面的气膜层有效长度最大弧度不超过10;°(3)吹风比对复合冷却效率有很大的影响,在冷却壁面冷却效率随吹风比的增加而增加,但当吹风比M>1.5时,吹风比对冷却效率的影响已不明显;(4)扰流柱的排列形式对冷却效果的影响不大。To theoretically study the heat transfer characteristics of impingement pin-fin＋reversed convection＋film cooling in curved section of combustion chamber,the flow and heat transfer characteristics of several models are analyzed by numerical simulation using fluent software,and the effects of geometry dimensions on film effectiveness are also studied.The research results show that：（1） The pin-fin between the impingement plate and the film hole plate greatly disturbs the flow in the impingement space,and the convection heat transfer between cooling flow and the heating wall is enhanced so the cooling effectiveness for the composite cooling structure is increased because of the pin-fin.（2） Under the geometrical dimension of this paper,the effect length of the cooling film on the curved heating wall is less than 10°.（3） The blowing ratio has a great effect on the effectiveness for the composite cooling structure,and the cooling effectiveness is increased with the increase of blowing ratio,but when the blowing ratio is larger than 1.5,the effect of blowing ratio on the effectiveness can be neglected.（4） The arrangement of pin-fin has little effect on cooling effectiveness.

关 键 词：回流燃烧室 弯曲段 扰流柱 复合冷却 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]