液液双组元同轴离心喷嘴启动过程仿真  

Simulation on the start⁃up process of the liquid⁃liquid bipropellant coaxial centrifugal nozzle

作　　者：石靖岩 张冰冰 鞠睿立 富庆飞[1,2,3] 李挺 SHI Jingyan;ZHANG Bingbing;JU Ruili;FU Qingfei;LI Ting(Beihang University,Beijing 100191,China;Beihang University,Ningbo Zhejiang 315100,China;National Key Laboratory of Aerospace Liquid Propulsion,Xi'an Shaanxi 710100,China)

机构地区：[1]北京航空航天大学,北京100191 [2]北京航空航天大学,浙江宁波315100 [3]航天液体动力全国重点实验室,陕西西安710100

出　　处：《航天工程大学学报》2025年第2期11-16,共6页

基　　金：先进航空发动机协同创新中心基础科研项目(501XTCX2023146001);国家自然科学基金资助项目(12272026);国家自然科学基金资助项目(U2341281)。

摘　　要：聚焦液体火箭发动机甲基肼/四氧化二氮(MMH/N2O4)自燃推进剂的喷注时序控制问题,基于Fluent仿真平台,采用流体体积法(VolumeofFluid,VOF)两相流模型和标准k-ε湍流模型,建立了离心式喷嘴内外路压降特性的数值模拟方法。通过系统分析液相分布、流场特征及出口速度演变规律,成功验证了燃料路较氧化剂路优先1.6ms喷注的设计目标。研究成果为优化发动机点火过程、预防集液腔爆炸风险提供了一定参考。This study focuses on the injection timing control of methylhydrazine/nitrogen tetroxide hypergolic(MMH/N2O4)propellants in liquid rocket engines.A numerical simulation method for the pressure drop characteristics of internal and external channels of a centrifugal nozzle was established using the Fluent simulation platform,incorporating the volume of fluid(VOF)multiphase flow model and the standard k-εturbulence model.Through systematic analysis of liquid phase distribution,flow field characteristics,and outlet velocity evolution,the design objective of achieving a 1.6 ms priority injection of the fuel channel over the oxidizer channel was successfully validated.Research findings provide valuable references for optimizing engine ignition processes and mitigating the risk of accumulation chamber explosions.

关 键 词：液体火箭发动机 甲基肼/四氧化二氮 离心喷嘴 数值模拟 流体体积法 

分 类 号：V557[航空宇航科学与技术—人机与环境工程]