固体火箭发动机熔渣沉积数值模拟

Numerical simulation of slag accumulation for solid rocket motors

关键词:  固体推进剂火箭发动机  二相流  潜入式喷管  沉积物

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

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。

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.