采用欧拉-拉格朗日方法的针栓推力室燃烧性能数值仿真

余航; 刘赟聪; 孙五川; 黄佐华; 李龙飞; 卞香港; 张英佳

doi:10.7652/xjtuxb202601017

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采用欧拉-拉格朗日方法的针栓推力室燃烧性能数值仿真

专题　“双碳”背景下的污染控制与资源化利用 | 更新时间：2026-01-15

- 采用欧拉-拉格朗日方法的针栓推力室燃烧性能数值仿真
- Numerical Simulation on Combustion Performance of Pintle Inj ector Thrust Chamber Using Euler-Lagrange Method
- 西安交通大学学报 2026年60卷第1期页码：171-179
- 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：
  
  作者简介：余航（1999—），男，硕士生；
  张英佳（通信作者），男，教授，博士生导师。
- 基金信息：
  
  国家自然科学基金“叶企孙”科学基金重点资助项目。(U2141203)
- DOI：10.7652/xjtuxb202601017
  中图分类号： V434+.13
- 收稿：2025-03-24，
  
  纸质出版：2026-01-10
- 稿件说明：
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余航, 刘赟聪, 孙五川, 等. 采用欧拉-拉格朗日方法的针栓推力室燃烧性能数值仿真[J]. 西安交通大学学报, 2026,60(1):171-179.

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.
余航, 刘赟聪, 孙五川, 等. 采用欧拉-拉格朗日方法的针栓推力室燃烧性能数值仿真[J]. 西安交通大学学报, 2026,60(1):171-179. DOI： 10.7652/xjtuxb202601017.

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

DRESSLER G A,BAUER J M.TRW pintle engine heritage and performance characteristics[C]//36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,VA,USA:AIAA,2000:AIAA 2000-3871.

谢远,聂万胜,姜传金,等.针栓式喷嘴喷雾燃烧特性研究进展[J].推进技术,2022 ,43(7):42-60.

XIE Yuan,NIE Wansheng,JIANG Chuanjin,et al. Research progress on spray combustion characteristics of pintle injector[J].Journal of Propulsion Technology,2022 ,43(7):42-60.

张波涛,李平,王凯,等.变推力液体火箭发动机中针栓喷注器研究综述[J].宇航学报,2020,41(12):1481-1489 .

ZHANG Botao,LI Ping,WANG Kai,et al.Review on pintle injector of throttling liquid rocket engine[J]. Journal of Astronautics,2020,41(12):1481-1489.

雷娟萍,兰晓辉,章荣军,等.嫦娥三号探测器7500 N变推力发动机研制[J].中国科学(技术科学), 2014,44(6):569-575.

LEI Juanping,LAN Xiaohui,ZHANG Rongjun,et al.The development of 7500 N variable thrust engine for Chang′E-3[J].Scientia Sinica (Technologica), 2014,44(6):569-575.

CHENG Peng,LI Qinglian,XU Shun,et al.On the prediction of spray angle of liquid-liquid pintle inj ectors[J].Acta Astronautica,2017,138:145-151.

ZHAO Fan,ZHANG Haibin,ZHAO Liang,et al.A new modeling method for spray angle prediction of liquid-liquid pintle injector[J].AIAA Journal,2023,61 (11):4960-4975.

陈慧源,李清廉,成鹏,等.动量比及其调节方式对针栓喷注器喷雾特性的影响[J].物理学报,2019,68 (20):209-222 .

CHEN Huiyuan,LI Qinglian,CHENG Peng,et al. Influence of momentum ratio and its throttling method on spray characteristics of pintle injector[J].Acta Physica Sinica,2019,68(20):209-222.

咸裕丰,孙冰.针栓式喷注器液氧/甲烷发动机燃烧特性数值仿真[J].推进技术,2021,42(7):1561-1569.

XIAN Yufeng,SUN Bing.Numerical simulation of combustion characteristics of LO X /CH engine with pintle injector[J ] .Journal of Propulsion Technology, 2021,42(7):1561-1569.

ZHOU Rui,SHEN Chibing.Influence of momentum ratio control mode on spray and combustion characteristics of a LO X /LCH 4 pintle injector[J ] .Journal of Zhejiang University-Science:A Applied Physics & Engineering,2 022,23(5):415-420.

俞南嘉,鲍启林,张洋,等.针栓式液氧/煤油发动机燃烧数值仿真[J].火箭推进,2018,44(4):23-29.

YU Nanjia,BAO Qilin,ZHANG Yang,et al.Numerical simulation of combustion for LO X /kerosene engine with pintle injector[J ] .Journal of Rocket Propulsion,2018,44(4):23-29.

HWANG D,KIM J,RYU C,et al.Geometric effects of liquid rocket engine pintle inj ectors in supercritical combustion[J].International Journal of Aeronautical and Space Sciences,2022,23(5):941-952.

张连博,毛晓芳,汪凤山,等.针栓喷注式MMH/NTO推力室燃烧及传热数值仿真[J].推进技术, 2015,36(10):1487-1494.

ZHANG Lianbo,MAO Xiaofang,WANG Fengshan, et al.Numerical simulation of pintle thruster combustion and heat transfer for MMH/NTO hypergolic bipropellant[J].Journal of Propulsion Technology, 2015,36(10):1487-1494.

XU Bo,CHEN Bing,PENG Jian,et al.A coupled heat transfer calculation strategy for composite cooling liquid rocket engine[J].Aerospace,2023,10 (5):473.

唐亮,王凯,刘计武,等.液膜冷却对火箭发动机燃烧效率的影响[J].火箭推进,2023,49(3):69-75.

TANG Liang,WANG Kai,LIU Jiwu,et al.Influence of liquid film cooling on combustion efficiency of rocket engine[J].Journal of Rocket Propulsion,2023,49 (3):69-75.

ZHANG Guodong,LI Guangxi,LI Longfei,et al. Thermal performance of MMH/NTO rocket thrust chamber based on pintle inj ector by using liquid film cooling[J]. Applied Thermal Engineering, 2023, 223:120035.

刘昌波,林革,宋大亮,等.针栓式推力室冷却特性试验研究[J].火箭推进,2020,46(1):13-19.

LIU Changbo,LIN Ge,SONG Daliang,et al.Experimental study on cooling characteristics of pintle thruster[J]. Journal of Rocket Propulsion,2020,46(1):13-19.

AMATO N A,LEYLEGIAN J C,NARAGHI M H. CFD analysis of film cooling and heat transfer in a bipropellant rocket nozzle,incorporating chemically reacting flow[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,VA,USA:AIAA,2016:AIAA 2016-4672.

JIAO Bowei,YU Nanjia,ZHOU Chuang,et al.Combustion flow field and thermal protection performance of a liquid oxygen/kerosene engine with pintle injectors[J]. Acta Astronautica,2024,225:928-941.

LIU Xinlin,SUN Jun,JIANG Zhuohang,et al.Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LO X /LCH 4 )rocket engine[J ] .Journal of Zhejiang University-Science:A,2024,25(8):631-649.

MANSU N,SUNDARARAJAN T,JAYACHANDRAN T.Numerical modeling of liquid film cooling heat transfer coupled to compressible gas[J].Lecture Notes in Mechanical Engineering,2024:845-860.

STROKACH E A,BOROVIK I N,BAZAROV V G, et al.Numerical study of operational processes in a GO x -kerosene rocket engine w ith liquid film cooling[J ] . Propulsion and Power Research,2020,9(2):132-141.

张波涛,唐亮,杨宝娥,等.动量比对单排槽针栓喷注器雾化特性的影响[J].科学技术与工程,2024,24 (3):1275-1282.

ZHANG Botao,TANG Liang,YANG Baoe,et al. Effects of momentum ratio on spray characteristics of pintle injector with single row slots[J].Science Technology and Engineering,2024,24(3):1275-1282.

ZHOU Rui,SHEN Chibing,JIN Xuan.Numerical study on the morphology of a liquid-liquid pintle injector element primary breakup spray[J].Journal of Zhejiang University-Science:A,2020,21(8):684-694.

林庆国.空间轨控发动机高效燃烧室仿真与试验研究[D].长沙:国防科学技术大学,2015.

安鹏,姚世强,王京丽,等.针栓式喷注器的特点及设计方法[J].导弹与航天运载技术,2016 (3):50-54.

AN Peng,YAO Shiqiang,WANG Jingli,et al.Characteristics and design of pintle injector[J].Missiles and Space Vehicles,2016(3):50-54.

张波涛,王凯,李平,等.径向槽布局方式对针栓喷注器雾化角的影响[J].火箭推进,2023,49(6):1-9.

ZHANG Botao,WANG Kai,LI Ping,et al.Effect of radial slots layout on spray angle for gas-liquid pintle injector[J].Journal of Rocket Propulsion,2023,49 (6):1-9 .

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