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.
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)
出处
《推进技术》
EI
CAS
CSCD
北大核心
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)
关键词
先进旋涡燃烧室
壁面冷却
掺混燃烧
Advanced Vortex Combustor
Wall cooling
Mixing and combustion
作者简介
通讯作者：曾卓雄，男，博士后，教授，研究领域为航空宇航推进理论与工程。E—mail：zengzhuoxiong@tsinghua．org．cn
