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

YU Hang; LIU Yuncong; SUN Wuchuan; HUANG Zuohua; LI Longfei; BIAN Xianggang; ZHANG Yingjia

doi:10.7652/xjtuxb202601017

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

Special Topic Pollution Control and Resource Utilization in the “Dual Carbon”Context | 更新时间：2026-01-15

- Numerical Simulation on Combustion Performance of Pintle Inj ector Thrust Chamber Using Euler-Lagrange Method
- Journal of Xi'an Jiaotong University Vol. 60, Issue 1, Pages: 171-179(2026)
- 作者机构：
  
  西安交通大学绿色氢电全国重点实验室，710049，西安
  西安航天动力研究所，710100，西安
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202601017
  CLC： V434+.13
- Received：24 March 2025，
  
  Published：10 January 2026
- 稿件说明：
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YU Hang, LIU Yuncong, SUN Wuchuan, et al. Numerical Simulation on Combustion Performance of Pintle Inj ector Thrust Chamber Using Euler-Lagrange Method[J]. Journal of Xi'an Jiaotong University, 2026, 60(1): 171-179.
DOI：

YU Hang, LIU Yuncong, SUN Wuchuan, et al. Numerical Simulation on Combustion Performance of Pintle Inj ector Thrust Chamber Using Euler-Lagrange Method[J]. Journal of Xi'an Jiaotong University, 2026, 60(1): 171-179. DOI： 10.7652/xjtuxb202601017.

摘要

针对带有边区液膜冷却的针栓式喷注器火箭发动机“效率-冷却”的固有矛盾，以甲基肼/四氧化二氮（MMH/NTO）针栓发动机为研究对象，采用

k-ω

SST湍流模型、欧拉-拉格朗日方法及涡耗散概念模型耦合多步化学反应机理，开展了推力室燃烧过程三维数值仿真研究，系统剖析了边路冷却比例和动量比对推力室性能的影响机制。研究结果表明：双排孔针栓喷注器的射流雾化结构呈现3个锥角的典型特征，燃烧高度依赖雾化掺混效果；随冷却比例增加，壁面温度显著降低，当冷却比例超过27%时，推进剂混合比偏离最佳值，推力室室压降低。综合考虑壁面温度安全性与推力室性能，边路冷却比例最优区间为20%～27%；动量比对推力室流场分布和燃烧效率影响显著，存在最佳动量比区间，偏离该区间均导致掺混效果不佳，进而使得推力室性能下降，双排孔针栓喷注器的建议动量比区间为2.10～3.06。该研究为MMH/NTO双组元针栓喷注推力室设计优化提供重要依据，为实现针栓发动机高效、安全运行提供工程指导，也为同类型姿轨控发动机性能优化提供设计参考。

Abstract

To address the inherent trade-off between efficiency and cooling in rocket engines with pintle inj ectors 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 wall 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 efficiency of the thrust chamber，with an optimal momentum ratio range identified.The recommended value for this configuration is 2.10—3.06.This study provides critical insights for the design optimization of MMH/NTO bipropellant pintle inj ector thrust chambers，offers engineering guidance for achieving efficient and safe operation of pintle engines，and serves as a design reference for performance optimization of similar attitude and orbit control engines.

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references

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