一种氢燃料微尺度非预混燃烧室数值模拟  

Numerical simulation investigation on a hydrogen micromix combustor

作　　者：莫妲 尚守堂 林宇震[2] 马宏宇 刘一雄 MO Da;SHANG Shoutang;LIN Yuzhen;MA Hongyu;LIU Yixiong(Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China;Research Institute of Aero-Engine,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]北京航空航天大学航空发动机研究院,北京100191

出　　处：《航空动力学报》2023年第11期2701-2710,共10页Journal of Aerospace Power

基　　金：先进航空动力创新工作站资助项目(HKCX2021-01-021)。

摘　　要：为降低航空发动机和地面燃机碳排放和NOx,提出一种多射流布局的氢燃料微尺度非预混燃烧室头部结构。为获得微尺度非预混燃烧组织机理,以及关键设计参数对燃烧性能的影响,采用k-ωSST(剪切应力输运)和FGM(火焰面生成流行)方法中的扩散火焰方法,通过9种组分共26步反应开展数值仿真模拟,对动量通量比、当量比、空气和氢气的导流板高度进行敏感性分析,探究氢气与空气的混合特性、火焰结构、温度分布、NOx排放的影响因素。对比分析了传统航空煤油与氢气NOx排放。结果表明:减小动量通量比有利于缩短火焰长度,可降低169.6%的NOx;存在一个空气导流板高度的临界值,使得NOx最高,在15%含氧量条件下NOx的体积分数为5×10^(-6);氢气导流板高度由3 mm增加为11 mm,NOx减少75.9%。与传统煤油相比,最优结构参数组合方案可进一步降低85.7%的NOx。In order to curb the carbon and NOx emissions of the aeroengine and ground gas turbines,a multi-injector combustor dome configuration was proposed.To explore the micromix non-premix combustion mechanism and the impacts of the critical parameters on the combustor performance,the k-ωSST(shear stress transfer)turbulence model,FGM(flamelet generated manifold)diffusion flamelet method and 9 species-26 steps reactions were adopted for the numerical simulation.Sensitivity analysis was performed with regard to the momentum flux ratio,equivalence ration,air-gate height and hydrogengate height.The influencing factors of mixing characteristics,flame structure,temperature distribution and NOx emission were explored.Meanwhile,the NOx emission between the conventional kerosene combustor and the hydrogen micromix was evaluated.Results showed that lower momentum flux ratio was beneficial for enhancing the mixing and reducing the flame length,resulting in 169.6%NOx reduction.There existed a critical value of the air gate height which brought about the highest NOx up to 5×10^(-6)under the 15%O2 content condition.As H2 gate height increased from 3 mm to 11 mm,NOx fell by 75.9%.Compared with the conventional kerosene combustor,NOx emission dramatically dropped by 85.7%,using the optimal combination of critical parameters.

关 键 词：氢燃料 微尺度非预混 NOx 动量通量比 导流板高度 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]