燃烧室头部两侧进气掺混气动特性  

Investigation on the mixing characteristics of combustion chamber with bilateral inlet at head

作　　者：靖建朋[1,2] 郭荣伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国人民解放军驻西安飞机工业公司军事代表室,西安710089

出　　处：《航空动力学报》2010年第9期1956-1963,共8页Journal of Aerospace Power

摘　　要：对一种燃烧室头部两侧进气掺混段的气动特性开展了数值仿真及试验验证,得到了掺混段在不同反压、来流马赫数、攻角及侧滑角下的性能参数和流场特征.结果表明,掺混段头部存在的横向旋涡是燃烧室火焰稳定和燃烧组织的关键,有攻角或侧滑角的情况下,掺混段的总压恢复有所下降,因此组织燃烧时应进行相应调节,以防止进气道进入不稳定工作状态.试验验证结果表明,仿真与试验的曲线规律一致,仿真研究结果可作为燃烧室设计和燃烧组织的依据.Numerical simulation and experimental verification of the mixing characteristics of combustion chamber with bilateral inlet at head were conducted in this study,the performance parameters and flow field characteristics of the mixing duct were obtained.The results show that the bilateral vortices at the head of the mixing duct is the key to ignition and flame stabilization,the total pressure recovery of the mixing duct decreases slightly under attack or yaw angle,so the combustion chamber shall allow to adjust the fuel quantity to avoid unstable working state of the inlet.It can be seen in the paper that the numerical results are consistent with the experimental results,indicating that the numerical simulation is feasible and can be used as a reference to the combustion chamber design and combustion organization.

关 键 词：燃烧室 两侧进气 掺混特性 总压恢复系数 数值仿真 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]