双凹腔超紧凑型涡轮级间燃烧室数值模拟  

Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Double Concave Cavity

作　　者：骆广琦[1] 曾剑臣 孟龙[1] 吴涛[1] 胡砷纛 

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《弹箭与制导学报》2016年第5期89-93,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了提高超紧凑型涡轮级间燃烧室在航空发动机的应用范围,文中在常规超紧凑燃烧室上引入驻涡燃烧,提出了一种双凹腔燃烧室。利用CFD技术对双凹腔燃烧室的三维两相流场和燃烧进行了数值模拟。结果表明:总压损失低至2.81%,燃烧室效率高达99.7%,气体温度提高685.7 K;出口径向温度随无量纲高度呈线性分布。与常规超紧凑燃烧室相比,双凹腔驻涡燃烧室具有更高的燃烧效率、出口温度和更低的总压损失。To improve application of ultra-compact interstage turbine burner in aero gas turbine engine, trapped vortex combustion in con- ventional ultra-compact combustor was introduced and a double concave cavity combustor was proposed. CFD was used to simulate three- dimensional two-phase combustion flow field and combustion in the combustor. The results show that gas temperature increases by 685.7 K with 2. 81% total pressure loss and 99. 7% combustion efficiency and radial temperature grows linearly with dimensionless height. Compared with conventional uhra-compact combustor, the double concave cavity combustor has higher combustion efficiency, exit temperature and lower total pressure loss.

关 键 词：驻涡燃烧 超紧凑 涡轮级间燃烧 数值模拟 

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]