前后翼型装药结构SRM气固两相流动特性

基于可压缩流动强守恒型Navier-Stokes方程，运用颗粒轨道模型（PTM）和shear stress transfer（SST）k-ω湍流模型，采用计算单元内颗粒源法（PSIC）进行气固两相耦合计算，建立了某型前后翼型装药结构固体火箭发动机（SRM）工作初期的三维两相内流场数值计算模型。对比分析了纯气相和气固两相条件下的SRM内部压强场、速度场、粒子沉积质量浓度和分布规律；重点研究了SRM燃烧室和喷管不同部位的颗粒沉积质量浓度，并考虑了不同颗粒物粒径、横向及纵向过载等因素的影响。结果表明:前后翼型装药结构SRM工作过程所产生的固体粒子主要集中于药柱前翼、后翼及筒段壁面；随着颗粒物粒径增加，各监测面上的粒子沉积质量浓度均升高；横向过载量与承载面最大颗粒沉积量呈正相关，且承载面和非承载面的粒子分布不均匀；随着轴向过载增加，颗粒物沿过载方向不断积累，逃逸率升高，沉积量降低；过载所引起的颗粒物方向偏转将同时影响燃烧室和喷管壁面的粒子沉积质量浓度，在前后翼型装药结构SRM绝热层设计中应充分考虑。 

Gas-solid two-phase flow characteristics of SRM propellant with front and rear wings

Based on the Navier-Stokes equation with strong conservation of compressible flow，the particle trajectory model （PTM） and shear stress transfer （SST） k-ω turbulence model were applied to calculate the gas-solid two-phase coupling by using the particle source method （PSIC） in the computational unit，and the three-dimensional two-phase flow field numerical calculation model of a type of solid rocket motor （SRM） with front and rear wings propellant at the ignition was established.The pressure field，velocity field，particle deposition mass concentrations and distributions under single-phase and two-phase conditions were compared and analyzed.The particle deposition mass concentrations in different parts of SRM combustion chamber and nozzle were studied，and the effects of different particle sizes，transvers and axial overloads were considered.The results showed that the solid particles produced by the front and rear wing SRM were mainly concentrated around the front wing，rear wing and the wall of the cylinder.With the increase of particle size，the particle deposition mass concentration on each monitoring surface increased.The transverse overload was positively correlated with the maximum particle deposition on the bearing surface，and the particle distribution on the bearing surface and the non-bearing surface was uneven.With the increase of axial overload，particles accumulated continuously along the overload direction，the escape rate increased，and the deposition decreased.The particle direction deflection caused by overload could affect the particle deposition mass concentration on the wall of combustion chamber and nozzle at the same time，which should be fully considered in the design of SRM insulation layer with front and rear wings charge propellant.