氢氧喷注器面板温度场的三维模型及计算分析

THREE-DIMENSIONAL MODEL FOR NUMERICAL ANALYSIS OF HEAT CONDUCTION AND ITS APPLICATIONS IN TEMPERATURE ANALOGY FOR INJECTOR FACE PLATE IN LOX/LH2 ROCKET ENGINES

关键词:  氢氧发动机  推力室  火箭推进剂喷嘴  温度分布  传热  数值分析  计算

Key words:  Hydrogen oxygen engine  Thrust chamber  Rocket propellant injector  Temperature distribution  Heat transfer  Numerical analysis  Computation

摘要:

本文推导了热传导的三维不等距网格差分公式,对氢氧发动机喷注器面板进行了通用的传热数值分析,得出了现行结构结冰是不可避免的.并且预测了一种新结构面板的温度场,它可以避免结冰.这种分析不仅对燃气发生器,而且对燃烧室同样适用,为今后喷注器设计提供了一种有效的传热分析手段.

Abstract:

In this paper, three-dimensional heat conduction finite difference equations for inequable length grid elements are derived from the partial differential equations. General-purpose heat transfer numerical analysis are carried out to the injector face plate in hydrogen/oxygen propellant rocket engines. Numerical analyses for the temperature distributions in the injector face plate of the experimental combustion chamber are proven out. The temperature distributions in the injector face plate of gas generator in hydrogen/oxygen propellant rocket engine are obtained, from which it is derived that freezing is unavoidable for the present construction. The temperature distributions in a new injector face plate little different from the present one in construction but prevented from freezing, is predicted. This analysis process is available not only for gas generators but for combustion chambers as well, providing an available method in heat transfer to the injector designs.