空气涡轮火箭发动机燃烧室异形尾缘波瓣混合器掺混、燃烧特性研究  

Mixing and combustion characteristics of special-shaped trailing lobe mixer in air turbine rocket engine combustor

作　　者：王敬新 胡斌[2,3] 王中豪 石强 尹必峰 赵庆军[2,3] WANG Jingxin;HU Bin;WANG Zhonghao;SHI Qiang;YIN Bifeng;ZHAO Qingjun(School of Automotive and Traffic Engineering,Jiangsu University,Zhenjiang 212013,China;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)

机构地区：[1]江苏大学汽车与交通工程学院,江苏镇江212013 [2]中国科学院工程热物理研究所,北京100190 [3]中国科学院大学航空宇航学院,北京100049

出　　处：《推进技术》2024年第10期136-147,共12页Journal of Propulsion Technology

基　　金：国家重点研发计划(2016YFB0901402)。

摘　　要：为了促进空气涡轮火箭发动机(ATR)燃烧室内涵富燃燃气与外涵空气之间的掺混,提高燃烧室燃烧效率,本文通过对波瓣进行尾缘修形设计,探究C形尾缘结构对波瓣下游流动及燃烧特性的影响规律。研究发现:(1)在波瓣混合器尾缘增加C形结构,会诱导产生多源副涡结构;(2)径向高度越高,径向速度梯度越大,造成副流向涡和副展向涡的强度和尺度越大;(3)由于受到C形尾缘结构诱导的副流向涡和副展向涡的影响,燃烧室展向截面温度分布出现“串状”局部高温区,燃烧得到强化;(4)当燃烧室距离与波瓣直径<1时,内、外涵气流掺混强烈,热混合效率、燃烧效率以及总压损失迅速增大;(5) C形尾缘结构数量与燃烧效率不成单调递增关系,当C形结构数量≤2时,副涡强化掺混起主导作用,燃烧效率随着副涡量的增大而增大;当C形结构数量≥3时,出口面积增大导致的涡量衰减起主导作用,燃烧效率随着副涡量的增大而减小。To improve the mixing between the fuel-rich gas in the internal channel and the air in the exter⁃nal channel of the air turbine rocket(ATR)combustion chamber,and enhance the combustion efficiency of the combustion chamber,this paper designs the trailing edge modification of lobes and explores the influence of Cshaped trailing edge structure on the downstream flow and combustion characteristics of lobes.The research finds that:(1)Adding a C-shaped structure to the trailing edge of the lobe mixer will induce the generation of multisource secondary vortex structures;(2)The higher the radial height is,the greater the radial velocity gradient is,resulting in larger strength and scale of secondary flow vortex and secondary spanwise vortex;(3)Influenced by the secondary flow vortex and secondary spanwise vortex induced by the C-shaped trailing edge structure,the temperature distribution in the cross section of the combustion chamber appears as"string-like"local high-tem⁃perature areas,and the combustion is intensified;(4)When the distance from the combustion chamber to the di⁃ameter of the lobe is less than 1,the internal and external airflows mix strongly,and the thermal mixing efficien⁃cy,combustion efficiency,and total pressure loss increase rapidly;(5)The number of C-shaped trailing edge structures does not have a monotonic increasing relationship with the combustion efficiency.When the number of C-shaped structures is not more than 2,the secondary vortex-enhanced mixing plays a leading role,and the combustion efficiency increases with the increase of the secondary vortex quantity;when the number of C-shaped structures is not less than 3,the attenuation of vortex quantity caused by the increase of outlet area plays a lead⁃ing role,and the combustion efficiency decreases with the increase of the secondary vortex quantity.

关 键 词：空气涡轮火箭发动机 波瓣混合器 C形尾缘结构 展向涡 流向涡 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]