基于动网格的喉栓式推力可调喷管内流场数值模拟  

Numerical simulation of pintle-controlled nozzle flow field based on dynamic grid

作　　者：唐金兰[1] 宋慧敏[1] 李进贤[1] 冯喜平[1] 

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2014年第5期634-639,共6页Journal of Solid Rocket Technology

基　　金：航天支撑技术基金(2011 1.3.2)

摘　　要：以FLUENT软件为工具,利用动网格技术,建立了喉栓式推力可调喷管内流场动态特性分析模型。通过网格的合并与分割,较好地解决了喉栓调节运动所导致的计算区域的瞬变问题,并分析了喉栓调节运动速度对喷管轴对称二维内流场动态特性的影响。分析结果表明,随着喉栓的调节运动,喷管内流场动态下的压强建立与稳态下的压强建立相比存在着明显的延迟,且随着喉栓调节运动速度的增大,延迟现象越明显。当喉栓完全进入喷管几何喉部位置时,喷管推力达到最大值。In order to study dynamic flow field of the pintle-controlled nozzle,physical model was established based on dynamic grid of FLUENT.Dynamic flow field of nozzle was simulated by the mesh of merging and splitting to solve computational flow transi-ent problems which was caused by pintle motion,and the effect of pintle motion velocity on 2D axisymmetric nozzle flow filed dynam-ic characteristics was analyzed.The results show that with the movement of pintle,the nozzle flow field changes significantly.With the increasing of the pintle velocity,there exist a significant hysteresis of pressure distribution in unsteady condition in comparison with steady condition,and when pintle velocity increases,the hysteresis increases.When the pintle is completely into the throat of the noz-zle geometry position,the thrust reaches to maximum value.

关 键 词：推力可调喷管 动网格 内流场 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]