进气交汇位置对固体火箭冲压发动机性能影响的仿真研究

Simulation Research on Influence of Inlets CrossingPosition on Solid Ducted Rocket Performance

通过对双下侧进气布局的固体火箭冲压发动机进气道进气交汇位置变化的各状态进行三维燃烧数值仿真,研究固定一次燃气时进气交汇位置对固体火箭冲压发动机性能的影响。仿真结果表明,进气交汇点从远离进气道一侧向靠近进气道变化时,固体火箭冲压发动机补燃室掺混燃烧程度将随之改变,导致补燃室出口温度场的畸变度先降低、后增加、再降低,当交汇点在补燃室中心时补燃室出口的不均匀度达到最大;同时发现发动机的推力与出口截面温度场的畸变度变化规律相反,即畸变度越低发动机性能越高;亦发现补燃室出口处温度场均匀时发动机喷管内的损失也会较低。

A 3D combustion simulation research about the varied inlets crossing positions of the solid ducted rocket with two inlets is carried out to study the influence of inlets crossing position on the performance of solid ducted rocket with fixed primary fuel injection.The performance of solid ducted rocket changes greatly when the crossing position moves from the side far away from the inlet to the side near the inlet.And the temperature field distortion at the outlet of the combustor declines at first,then it rises,but it decreases in the end.When crossing position is at the center of the combustor,the nonuniformity of the combustor outlet reaches the maximum.While the performance of solid ducted rocket opposites with the temperature field distortion,that means,the lower the distortion,the higher the engine performance.When the temperature field at the combustor outlet is uniformity,the less nozzle lost would be gotten as well.