TY - JOUR
T1 - 基于CFD-DEM算法的固体火箭发动机气-固两相流模拟
AU - Yang, Wen Jing
AU - Kuang, Liang
AU - Chu, Kai Wei
AU - Liu, Pei Jin
N1 - Publisher Copyright:
© 2019, Editorial Department of Journal of Propulsion Technology. All right reserved.
PY - 2019/7/1
Y1 - 2019/7/1
N2 - The multi-phase flow in Solid Rocket Motor (SRM) is a typical complex multi-scale flow, which plays an important role in influencing the performance and safety of SRM. The particle erosion on ablate layer and the thrust lose of gas-particle flow are the long-term concerns in solid propellant system. Compared to the conventional Two Fluid Model (TFM) and Lagrange Method, the Discrete Element Method (DEM) based gas-particle simulation is able to describe the particle behavior on microscopic level, such as particle-particle collides, particle-gas interaction force and particle-wall interaction force, and hence it has extensive applications in different areas. The Computational Fluid Dynamic (CFD) is coupled with DEM to predict the gas-particle flow in SRM. The results indicate that compared to the conventional methods, CFD-DEM could provide rich information, such as particle-particle contacts, particle-gas interactions, and all sorts of forces acted on particles. Particles are accumulated in the wall region of nozzle convergent part, in the throat, and in the central area of nozzle divergent part, which subsequently leads to frequent collides among particles and high angular velocity of particles. Drag force appears higher in the region where gas is accelerated. CFD-DEM simulation provide a new way to study the gas-particle flow in SRM, and reveal rich information on micro- and macro-level, thus would deliver new perspectives to understand the multi-phase flow in SRM, the particle erosions and so on.
AB - The multi-phase flow in Solid Rocket Motor (SRM) is a typical complex multi-scale flow, which plays an important role in influencing the performance and safety of SRM. The particle erosion on ablate layer and the thrust lose of gas-particle flow are the long-term concerns in solid propellant system. Compared to the conventional Two Fluid Model (TFM) and Lagrange Method, the Discrete Element Method (DEM) based gas-particle simulation is able to describe the particle behavior on microscopic level, such as particle-particle collides, particle-gas interaction force and particle-wall interaction force, and hence it has extensive applications in different areas. The Computational Fluid Dynamic (CFD) is coupled with DEM to predict the gas-particle flow in SRM. The results indicate that compared to the conventional methods, CFD-DEM could provide rich information, such as particle-particle contacts, particle-gas interactions, and all sorts of forces acted on particles. Particles are accumulated in the wall region of nozzle convergent part, in the throat, and in the central area of nozzle divergent part, which subsequently leads to frequent collides among particles and high angular velocity of particles. Drag force appears higher in the region where gas is accelerated. CFD-DEM simulation provide a new way to study the gas-particle flow in SRM, and reveal rich information on micro- and macro-level, thus would deliver new perspectives to understand the multi-phase flow in SRM, the particle erosions and so on.
KW - Discrete element method
KW - Gas-particle flow
KW - Numerical simulation
KW - Solid rocket motor
UR - http://www.scopus.com/inward/record.url?scp=85071949730&partnerID=8YFLogxK
U2 - 10.13675/j.cnki.tjjs.180645
DO - 10.13675/j.cnki.tjjs.180645
M3 - 文章
AN - SCOPUS:85071949730
SN - 1001-4055
VL - 40
SP - 1546
EP - 1553
JO - Tuijin Jishu/Journal of Propulsion Technology
JF - Tuijin Jishu/Journal of Propulsion Technology
IS - 7
ER -