摘要
通过考虑流场与壁面的湍流换热、固壁中的热传导以及包含吸收-发射性气体介质的喷管空腔中的热辐射交换等因素,建立了喷管喉衬流固耦合换热模型,通过与前人实验结果对照验证了模型的准确性;应用该模型分析了喷管粗糙度、燃气组分、燃烧室压强、推进剂燃温等因素对喷管喉衬热结构及换热规律的影响。仿真结果表明,喷管喉衬壁面温度和总热流密度在喷管喉部直段的前端达到最大;上述因素对喷管喉衬热交换的热流密度影响很大。
The heat transfer liquid-solid coupling model was built by considering many factors, which are the turbulence heat exchange between flow and wall, the heat conduction of the wall and the thermal radiation exchange of the gas in the flow area. And the model was verified by the experiment results. The impacts of work conditions on throat heat structure were researched. The simulation results and their analysis indicate preliminarily that both the wall temperature and total heat flux of nozzle throat reach the highest values at the head of the straight segment, and such factors as roughness, gas composition, the pressure of combustion chamber and combustion temperature affect the total heat flux per unit time greatly.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2014年第1期23-28,共6页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(50976095)资助
关键词
数值模型
实验验证
数值仿真
喷管喉衬
壁面温度
热流密度
computer simulation, errors, experiments, heat conduction, heat flux, heat radiation, heat transfer, mathematical models, Navier-Stokes equations, numerical methods, pressure, rocket engines, rocket nozzles, schematic diagrams, solid propellants, surface roughness, temperature, temperature distri bution, turbulent flow
nozzle throat, wall temperature
