高温多组分混合气体热导率理论预测
Theoretical Prediction of Thermal Conductivity of High Temperature Multi-component Gas Mixture
缐磊 1曹涛锋 2陈磊 1陶文铨1
作者信息
- 1. 西安交通大学能源与动力工程学院,热流科学与工程教育部重点实验室,西安 710049
- 2. 西安航天动力技术研究所,固体推进全国重点实验室,西安 710100
- 折叠
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H2、CO以及N2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.
Abstract
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 H2,CO,and N2 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.
关键词
燃烧气体/高温/热导率/火箭发动机Key words
combustion gas/high temperature/thermal conductivity/rocket engine引用本文复制引用
出版年
2024
NETL
NSTL
万方数据