液体火箭贮箱多路虹吸出流方案仿真与试验研究

Numerical simulation and experimental research on the tank with multiple siphon discharge devices

针对传统盖板类出流方案下贮箱低温推进剂剩余量较多的问题,基于Flow 3D流体仿真软件,通过引入旋转扰动模拟实际出流过程中外界环境产生的扰动,采用大涡模拟仿真模型对多路虹吸出流方案进行了数值分析。仿真结果表明,贮箱推进剂出流状态与管路布局有关,局部出流效应越显著,液面越易失稳产生漩涡造成输送管提前夹气。在此基础上,开展了地面原理性试验,试验结果复现了七路无漩、单路有漩等出流特性,验证了仿真结果的有效性。同时针对典型的单路有漩工况,开展了消漩叶片的漩涡抑制效果研究。研究表明,消漩叶片具有明显的漩涡抑制功能,可有效降低贮箱的推进剂剩余量。

In response to the problem of a large amount of low-temperature propellant remaining in fuel tank with tradition-al discharge devices,numerical analysis of multiple siphon discharge schemes was conducted by using a large eddy simulation model.The simulation was based on the fluid simulation software,and the disturbance generated by the external environment dur-ing the actual discharge process was simulated by introducing rotational disturbances.The simulation results show that flow state of propellant is related to the layout,which means that the more significant the local discharge effect,the easier to generate vorti-ces,which resulting papeline claped early.On this basis,ground experiments were carried out,and the experimental results repro-duced the flow characteristics of seven channels without vortices and one channel with vortices,verifying the effectiveness of the simulation results.Meanwhile,The vortex suppression effect of vortex shedding blades was studied under the conditions of typical single channel vortex.The results show that the vortex shedding blades have obvious vortex suppression function,which can ef-fectively reduce the remaining propellant in the storage tank.