热沉式超燃冲压发动机非稳态热-结构分析

Unsteady thermal-structural analysis of heat sink scramjet

为了评估热沉式超燃冲压发动机非稳态热-结构特性,初步发展了数值模拟方法。将AHL3D计算的超燃发动机三维内流场结果作为输入条件,然后通过参考焓法得到热环境数据,最后将发动机流道的热环境数据和压载数据输入到热/力响应有限元计算程序。通过对地面试验发动机的非稳态热分析计算结果表明,数值模拟方法适用性较好;沿轨道飞行发动机在发动机点火前机体最大温度可达825 K,喷涂绝热涂层能够降低机体温度;发动机机体的应力和位移随着时间的增加而增大。

In order to evaluate the unsteady thermal-structural characteristics of the heat sink scramjet,a numerical model has been preliminarily developed.Three dimensional internal flow results of scramjet from AHL3D can be served as an input,then thermal environmental data can be obtained by eckert reference enthalpy method.Finally thermal environmental data and pressure data along scramjet flow path can be introduced into the thermal-stress finite element program.The results show that the numerical model is applicable.The maximum temperature of scramjet along orbits can reach 825 K.Coating can reduce the temperature of scramjet.The stress and displacement of scramjet can be increased with the increment of time.