回流燃烧室流动特性试验  

Experiment on flow characteristics of a reverse-flow combustor

作　　者：翟维阔 胡阁 彭剑勇 金武 汤朝伟 李建中[2] ZHAI Weikuo;HU Ge;PENG Jianyong;JIN Wu;TANG Chaowei;LI Jianzhong(Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航空发动机集团有限公司湖南动力机械研究所,湖南株洲412002 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2019年第10期2081-2090,共10页Journal of Aerospace Power

摘　　要：为了揭示有/无燃烧状态下燃烧室热态和冷态流场的特征和流动特性,针对某型回流燃烧室单头部试验件,使用粒子图像测速仪(PIV),测量燃烧室燃烧状态下不同截面处的热态流场,以及没有燃烧状态下不同截面处的冷态流场,探讨不同总压损失系数对回流燃烧室热态/冷态流场特征及流动特性的影响。研究表明:随着总压损失系数的增大,冷态条件下各截面流场结构基本保持不变,如射流孔穿透深度、射流角度、回流区位置及大小、流线等基本保持一致,但是各位置点速度大小逐渐增大。热态条件下各截面流场随着总压损失系数增大,流场结构也基本保持不变;相同总压损失系数时,热态流场与冷态流场存在差异,燃油喷射与气流的相对运动将会对燃烧室头部的流场结构造成影响,速度较冷态流动时略微增大。To reveal the flow field differences and flow characteristics between the nonreacting flow and the reacting flow,the flow fields at different sections of a reverse-flow combustor with different total pressure loss conditions were measured and investigated through particle image velocimetry(PIV)measurement technology.The result showed that:with the increase of the total pressure loss,the non-reacting flow field in the specific section was consistent,the penetrating depth,jet angle,reverse-zone position and size,and the flow line were all similar.Otherwise,the velocity rose.And the reacting flow field in the specific section was also consistent with the increase of the total pressure loss.Also there were some differences from the reacting flow field to the non-reacting flow field in the same total pressure loss condition.The relative motion of fuel injection and airflow will affect the flow field structure of the head zone of the combustor,and the velocity of reaction is faster than the non-reaction.

关 键 词：回流燃烧室 总压损失系数 粒子图像测速仪(PIV) 热态流场 冷态流场 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]