摘要
Abstract
Aiming for predicting two-phase loss within the large nozzles of solid rocket motors,a computational methodology based on the Eulerian-Lagrangian framework was proposed.Initially,the effects of varying the number of solid particle parcels in the simulation,the model's dimensionality(three-dimensional or two-dimensional axial symmetry),and the solid particle heat transfer model were studied.The model and parameters suitable for accurately calculating two-phase loss in large nozzle configurations were obtained.Subsequently,the influence of critical particle parameters on nozzle performance was investigated.The findings reveal that the two-phase loss increases from 3.73%for particles with a diameter of 1 μm to 11.38%for particles with a diameter of 20 μm.Concurrently,the two-phase loss with a particle diameter of 5 μm,rises from 0.77%at a particle mass fraction of 10%to 5.82%at a mass fraction of 30%.Finally,a rapid calculation method tailored for nozzle contour optimization was developed,employing a seg-mented computational approach to map gas and particle phase data from the upstream transonic segment to the inlet of the down-stream supersonic segment,which significantly reduced the prediction time for two-phase loss in large nozzles.The method was also applied to perform numerical calculations on three different nozzle contours,rapidly obtaining the thrust and specific impulse per-formance parameters for each contour.This verifies the practical value of the method in nozzle performance optimization and demon-strates its feasibility in nozzle contour optimization design.关键词
固体火箭发动机/喷管两相流损失/气固两相流/欧拉-拉格朗日模型/喷管型面优化Key words
solid rocket motor/nozzle two-phase loss/gas-solid two-phase flow/Eulerian-Lagrangian model/nozzle contour opti-mization分类
航空航天
