非平衡效应下固体火箭发动机喷管两相流损失及其快速预示  

Non-equilibrium effects on two-phase flow losses in solid rocket motor nozzles and their rapid prediction

作　　者：马泽遥 陈晓东 MA Zeyao;CHEN Xiaodong(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《固体火箭技术》2025年第2期205-215,共11页Journal of Solid Rocket Technology

摘　　要：针对固体火箭发动机大型喷管两相流损失预示问题,构建了基于欧拉-拉格朗日的喷管两相流计算模型。对模型中的固体颗粒包裹数量、模型维度(三维或二维轴对称)和颗粒传热模型的影响进行了研究,得到了适用于大型喷管两相流损失预示的模型和参数,研究了关键颗粒参数对喷管性能的影响。结果表明:两相流损失由颗粒粒径为1μm时的3.73%提高到粒径为20μm时的11.38%;在粒径为5μm工况下,两相流损失由颗粒质量浓度10%时的0.77%提高到浓度30%时的5.82%。最后,开发了一种适用于喷管型面优化的两相流损失快速预示方法,使用分段计算方法将上游跨声速段气相和颗粒相数据映射到下游超声速段的入口,该方法进一步减小了大型喷管两相流损失预示的时间。运用该方法对三种不同喷管型面进行了数值计算,快速获取了各型面的推力和比冲性能参数,验证了该方法在喷管性能优化中的实用价值,证实了其在喷管型面优化设计中的可行性。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 1μm to 11.38%for particles with a diameter of 20μm.Concurrently,the two-phase loss with a particle diameter of 5μm,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 segmented computational approach to map gas and particle phase data from the upstream transonic segment to the inlet of the downstream 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 performance parameters for each contour.This verifies the practical value of the method in nozzle performance optimization and demonstrates 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 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]