采用欧拉-拉格朗日方法的针栓推力室燃烧性能数值仿真

打开文本图片集

关键词：姿轨控发动机;针栓式喷注器；甲基胖/四氧化二氮；三维数值仿真中图分类号： V434+.13 文献标志码：ADOI：10.7652/xjtuxb202601017 文章编号：0253-987X（2026）01-0171-09

Numerical Simulation on Combustion Performance of Pintle Injector Thrust Chamber Using Euler-Lagrange Method

YU Hang1，LIU Yuncong1，SUN Wuchuan1，HUANG Zuohua1，LI Longfei² ， BIAN Xianggang²，ZHANG Yingjial 1.State Key Laboratory of Multiphase Flow in Power Enginering，Xi'an Jiaotong University，Xi'an 710049，China; 2.Xi'an Aerospace Propulsion Institute，Xi'an 7loloo，China）

Abstract： To address the inherent trade-off between efficiency and cooling in rocket engines with pintle injectors featuring peripheral liquid film cooling，a three-dimensional numerical simulation of combustion processes in the thruster chamber of an monomethylhydrazine/nitrogen tetroxide （MMH/NTO） pintle engine is conducted using the Euler-Lagrange approach coupled with a multi-step chemical reaction mechanism. The influence mechanisms of the peripheral cooling ratio and momentum ratio on thrust chamber performance are systematically analyzed. The results show that as the cooling ratio increases，the wall temperature significantly decreases. However， when the cooling ratio exceeds 27% ，the propellant mixture ratio deviates from the optimal value，leading to a reduction in chamber pressure. Considering both wal temperature safety and thrust chamber performance， the optimal range for the peripheral cooling ratio is 20%-27% The study also reveals that the momentum ratio significantly affects the flow field distribution and combustion eficiency of the thrust chamber，with an optimal momentum ratio range identified. The recommended value for this configuration is 2.1O—3.O6. This study provides critical insights for the design optimization of MMH/NTO bipropellant pintle injector thrust chambers，offers engineering guidance for achieving eficient and safe operation of pintle engines，and serves as a design reference for performance optimization of similar attitude and orbit control engines.

Keywords： attitude and orbit control engine； pintle injector； monomethylhydrazine/nitrogen tetroxide；three-dimensional combustion numerical simulation

针栓式喷注器凭借其优异的推力调节性能、制造便利性和高工作可靠性，被广泛应用于变推力姿轨控飞行器。（剩余13141字）