三组元发动机氢的质量分数对燃烧流场影响的数值研究  

Numerical study of effect of hydrogen fraction on combustion field of tripropellant rocket engine

作　　者：林志勇[1] 周进[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《热科学与技术》2004年第1期81-85,共5页Journal of Thermal Science and Technology

摘　　要：用三维湍流 N - S方程以及颗粒轨道模型描述气氢 /煤油 /液氧三组元发动机内部喷雾两相湍流燃烧过程。气相化学反应速率由 Arrhenius公式计算。采用 19步详细反应动力学模型来描述氢氧反应 ,三步总包反应模型来描述煤油与氧反应。通过耦合求解气液两相流模型方程 ,得到了三组元发动机的燃烧流场 ,并与热试结果进行了比较验证。同时分析比较了增加氢的质量分数三组元工况以及只有煤油 /液氧的两组元工况下的不同流场特性。研究结果表明 ,在煤油燃料中增加适量的氢有利于缩短煤油液滴蒸发距离 。Two phase turbulent combustion process of GH/LO X /RP 1 tripropallent rocket engine was simulated with three dimension N S equations and discrete particles model. Chemical reaction was modeled with Arrhenius formulation. Detailed 19 steps chemical mechanism was used to describe the reaction of hydrogen and oxygen and the three steps global combustion model was used to simulate the reaction of kerosene and oxygen. The combustion field of tripropellant engine was obtained with coupled two phase equations and was validated by the hot experiments result. The different characteristics of tripropellent condition with different hydrogen fraction and RP/LO x bipropellant condition were analyzed. The result shows that adding the fraction of hydrogen to the fuel will increase the vaporing rate of kerosene, and thus will enhance the combustion performance.

关 键 词：三组元火箭发动机 喷雾燃烧 数值模拟 燃烧性能 物理模型 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]