固体火箭发动机熔渣沉积数值模拟

推进技术 ›› 2002, Vol. 23 ›› Issue (5): 366-369.

固体火箭发动机熔渣沉积数值模拟

向红军,方国尧

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15
基金资助:
国家重点实验室基金(97JS60 2 2 HK01)。

Numerical simulation of slag accumulation for solid rocket motors

School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China

Published:2021-08-15

摘要/Abstract

摘要： 为了探求熔渣沉积的机理,采用欧拉拉格朗日两相方法模拟带潜入喷管的固体火箭发动机两相内流场。通过对发动机工作后期六个时刻的两相流动与粒子轨迹计算,得到了三种Al2O3重附着率(0 2,0 4,0 6)下的潜入喷管背壁熔渣沉积总量分别为0 14%,0 48%和0 91%,提出了减少熔渣沉积的一些途径。

关键词: 固体推进剂火箭发动机;二相流;潜入式喷管;沉积物

Abstract: In order to gain a better estimate of SRM slag accumulation, an Eulerian Lagrangian two phase approach was adopted to simulate the two phase internal flow in a solid rocket motor with submerged nozzle. The two phase flow field and trajectories of particles were predicted at six burn times, and slag weight (014%,048% and 091%) retained in back wall region of submerged nozzle were calculated with three values (02,04,06) of Al2O3 re attachable fraction. Some special treatments are suggested to reduce the slag accumulation.

Key words: Solid propellant rocket engine;Two phase flow;Insert nozzle;Precipitate

向红军,方国尧. 固体火箭发动机熔渣沉积数值模拟[J]. 推进技术, 2002, 23(5): 366-369.