液体火箭推力室面板发汗冷却与燃烧耦合数值模拟  

Numerical Investigation of Transpiration Cooling Coupled With Combustion in the Thrust Chamber of Liquid Rocket

作　　者：祝银海[1] 姜培学[1] 孙纪国 熊宴斌[1] 

机构地区：[1]热科学与动力工程教育部重点实验室清华大学热能工程系,北京100084 [2]北京航天动力研究所,北京100076

出　　处：《工程热物理学报》2012年第1期101-104,共4页Journal of Engineering Thermophysics

基　　金：国家自然科学基金重点资助项目(No.50736003)

摘　　要：对推力室的喷嘴多孔面板的发汗冷却和燃烧室内的燃料燃烧过程进行了耦合数值计算,建立了一个带燃烧的三维、真实气体、变物性的推力室CFD计算模型。利用UDF编写了CH_4、O_2、CO_2、H_2O气体的实际气体状态方程,并根据NIST物性数据拟合了不同温度和压力下各气体的比热容、扩散系数、黏性系数和导热系数等物性多项式。基于EDC模型建立了甲烷-氧燃烧的多步反应机理。计算了三种厚度的面板和多种燃料进口工况下的推力室内的发汗冷却和燃烧过程,研究了面板厚度、冷却剂进出条件等因素对发汗冷却和燃烧过程的影响规律。The transpiration cooling in the porous meal mesh platelet was numerically investigated coupled with the combustion process in the thrust chamber of the liquid rocket. A 3D CFD model of the thrust chamber based on the real gas relations was established. The real gas equations and the thermophysical properties of CH4, O2, CO2 and H2O were programmed in UDF under various temperatures and pressures. The combustion mechanism of CH4 and O2 was modelled based on the EDC model. The numerical studies on the transpiration cooling and the combustion process were calculated at various fuel inlet conditions and three platelets. The effects of the inlet condition and the platelet thickness on the transpiration cooling and the combustion characteristics were analyzed.

关 键 词：推力室 丝网多孔 发汗冷却 燃烧 数值模拟 

分 类 号：TK124[动力工程及工程热物理—工程热物理]