固体火箭发动机摆动喷管两相流场与性能分析

Two-phase Flow and Performance Characteristics in a Gimbaled Nozzle of Solid Rocket Motor

为研究固体火箭发动机燃气流对摆动喷管性能的影响规律,运用离散相模型对摆动喷管内复杂三维两相流动进行数值仿真,重点分析了不同摆角下凝相粒子浓度与粒径的影响。结果表明,喷管有无摆动时,喷管效率均随粒子浓度和粒径的增大而下降,推力系数随粒子浓度增大而增大;无摆动时,推力系数不随粒径变化,摆动5°后,随粒径增大而下降。此外,小粒径粒子可增强矢量特性,而大粒径粒子抑制了喷管矢量特性。

In order to study the gimbaled nozzle’s performance characteristics under the gas,producing by solid rocket motor(SRM).The Discrete Phase Model was used to numerically investigate the complicated muli-phase flow fields in the gimbaled nozzle.The influence of condensed particle’s size and concentration were discussed,when the nozzle without swing or swinging 5 degrees.Results indicate that,no matter the nozzle swings or not,with the increase of the particle’s size and concentration,the nozzle efficiency decrease obviously,but the thrust coefficient increase as the concentration of particle increasing.When the nozzle without swing,the thrust coefficient wouldn’t change with the size of the condensed particle,however,it will decrease with the enlarging size of particle,when the nozzle swings 5 degrees.Moreover,the trajectories of the small particles vary little with the swinging nozzle’s gas flow,amplifying the vector angle,while the big particles obeys an inverse law.