摘要
准确获取高温燃气的热学性质是开展火箭发动机喷管数值仿真的基础。由于采用实验方法获取高温下气体热导率极其困难,基于理论计算手段预测高温下气体热导率成为更好的选择。本研究中,使用考虑高温电子激发态的Istomin修正计算了H_(2)、CO以及N_(2)气体在300~4000 K温度范围内的热导率。结合Wassiljewa方程构建了高温下多组分混合气体导热性质理论预测模型,预测了两种燃烧气体在300~4000 K温度范围的混合气体热导率,为喷管精细化仿真提供燃气热学性质参考数据。
Accurately obtaining the thermal properties of high-temperature gas is the basis for numerical simulation of rocket engine nozzles.Since it is extremely difficult to obtain the thermal conductivity of gas at high temperature by experimental methods,it is a better choice to predict the thermal conductivity of gas at high temperature based on theoretical calculation methods.In this study,the thermal conductivities of H_(2),CO,and N_(2) gases in the temperature range of 300 K to 4000 K were calculated using the Istomin correction considering high-temperature electronic excited states.Combined with the Wassiljewa equation,a theoretical prediction model for the thermal conductivity of multi-component gas mixtures at high temperatures was constructed,and the thermal conductivity of the gas mixtures of the two combustion gases in the temperature range of 300K to 4000K was predicted,providing gas reference thermal property data for the refined simulation of the rocket engine nozzle.
作者
缐磊
曹涛锋
陈磊
陶文铨
XIAN Lei;CAO Taofeng;CHEN Lei;TAO Wenquan(Key Laboratory of Thermo-Fluid Science and Engineering,MOE,School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China;National Key Laboratory of Solid Rocket Propulsion,The Institute of Xi’an Aerospace Solid Propulsion Technology,Xi’an 710100,China)
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2024年第8期2460-2465,共6页
Journal of Engineering Thermophysics
关键词
燃烧气体
高温
热导率
火箭发动机
combustion gas
high temperature
thermal conductivity
rocket engine
