摘要
为了促进空气涡轮火箭发动机燃烧室内来自压气机的空气和流经涡轮的富燃燃气的掺混与燃烧,基于空气涡轮火箭发动机燃烧室入口结构参数设计了波瓣混合器,并采用数值模拟方法通过调整张角及瓣宽比对波瓣结构进行优化。结果表明:(1)保持外张角不变,增大波瓣内张角可以有效改善内涵燃料在燃烧室中心轴附近区域燃烧不完全的状况;(2)在内、外张角相同的条件下,通过减小瓣宽b_(2)使瓣宽比B大于1可以提升掺混及燃烧效率;(3)相对于非反应流动,波瓣诱导流向涡在反应流中强度更高,沿径向向外移动的速度也更快;(4)带有波瓣结构的燃烧室内,因内、外涵气流掺混造成的总压损失很小,80%以上的总压损失是由加热造成的。
The lobed mixers were designed based on the ATR combustor inlet structure to facilitate the mixing and combustion of the air from the compressor and the fuel-rich gas from the turbine,and the numerical methods were used. The structure of lobe was optimized by increasing the penetration angle and the lobe width ratio.The relevant results show that:(1)Keeping the inner penetration angle constant and increasing the inner penetration angle,the status of incomplete combustion in the center area of the combustor can be alleviated effectively.(2)Keeping the inner and outer penetration angles constant and decreasing the lobe width b_(2) at the trailing edge so that the lobe width ratio B is less than 1 can increase the mixing and combustion efficiencies.(3)Compared with the non-reacting flow,the streamwise vortex induced by the lobed mixer has higher intensity and radial velocity in the reacting flow.(4)In combustors with the lobed mixers,the total pressure loss caused by the mixing between the core and bypass flows is small,more than 80% of total pressure loss is caused by the heating process.
作者
陈幸
胡斌
王中豪
赵巍
赵庆军
CHEN Xing;HU Bin;WANG Zhong-hao;ZHAO Wei;ZHAO Qing-jun(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2021年第12期2744-2753,共10页
Journal of Propulsion Technology
基金
国家重点研发计划(2016YFB0901402)
国防基础科研计划(JCKY2018603C13)。
作者简介
陈幸,硕士生,研究领域为空气涡轮火箭发动机燃烧室;通讯作者:赵庆军,博士,研究员,研究领域为航空发动机气动热力学。
