冷气入射角及射流比对先进驻涡燃烧流动的影响  

Effects of Cold Flow Injection Angle and Injection Ratio on Combustion Flow in Advanced Vortex Combustor

作　　者：曾卓雄 王志凯 ZENG Zhuo-xiong;WANG Zhi-kai(College of Power and Mechanical Engineering,Shanghai University of Electric Power,Shanghai 200090,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China)

机构地区：[1]上海电力学院能源与机械工程学院,上海200090 [2]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《推进技术》2018年第8期1797-1802,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(51066006;51266013);航空科学基金(2013ZB56002;2013ZB56004)

摘　　要：为了获得带导流片的先进旋涡燃烧室(AVC)壁面气膜冷却效率的变化规律,对不同冷空气入射角度以及射流比下的绝热壁面AVC冷却及掺混燃烧性能进行了数值模拟及分析。结果表明:入射角等于30°时,射流比越大压损越小;入射角等于60°时,压损相差不大;入射角等于90°时,射流比越大压损越大。入射角等于30°时,燃烧效率受射流比的影响较小;入射角等于90°时,燃烧效率随着射流比的增大而增大。射流比等于1.2及1.5时,燃烧效率随入射角的变化幅度较小;射流比等于1.8及2.0时,燃烧效率随入射角的增大而增大。In order to obtain wall film cooling efficiency in Advanced Vortex Combustor（AVC）with flow guide vanes,numerical investigation was performed on the cooling and mixing combustion performance in AVC in the condition of different injection angles and injection ratios. The results show that when the injection angle is equal to 30°,the pressure loss decreases with the increase of the injection ratio,but the combustion efficiency is less affected. When the injection angle equals 60°,the pressure loss varies little,but when the injection angle is equal to 90°,the pressure loss and the combustion efficiency both increase. With the increase of the injection angle,when the injection ratio is equal to 1.2 and 1.5,the combustion efficiency varies slightly,but when the injection ratio is equal to 1.8 and 2,the combustion efficiency increases.

关 键 词：先进旋涡燃烧室 壁面冷却 掺混燃烧 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]