Effects of throttling level on spray characteristics of gas⁃liquid pintle injector unit

Botao ZHANG; Ping LI; Anlong YANG; Baoe YANG

doi:10.13224/j.cnki.jasp.20210235

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Effects of throttling level on spray characteristics of gas⁃liquid pintle injector unit

Rocket Engine | 更新时间：2025-04-07

- Effects of throttling level on spray characteristics of gas⁃liquid pintle injector unit
- Journal of Aerospace Power Vol. 37, Issue 4, Pages: 791-801(2022)
- 作者机构：
  
  1.中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室，西安 710100
  2.中国航天科技集团有限公司航天推进技术研究院，西安 710100
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210235
  CLC：
- 稿件说明：
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Botao ZHANG, Ping LI, Anlong YANG, et al. Effects of throttling level on spray characteristics of gas⁃liquid pintle injector unit[J]. Journal of Aerospace Power, 2022, 37(4): 791-801.
DOI：

Botao ZHANG, Ping LI, Anlong YANG, et al. Effects of throttling level on spray characteristics of gas⁃liquid pintle injector unit[J]. Journal of Aerospace Power, 2022, 37(4): 791-801. DOI： 10.13224/j.cnki.jasp.20210235.

摘要

为了分析气液针栓喷注单元雾化特性和雾化机制，采用背光成像技术和相位多普勒（PDA）系统进行试验研究，获得了雾化模式、体积流量分布、索泰尔平均直径（SMD）分布和速度场随节流水平的变化规律。结果表明：气液针栓喷注单元雾场形态为扇形雾场，雾化模式为剪切破碎。体积流量沿径向呈单峰形分布，随着节流水平降低，雾场外缘向中心收缩。SMD沿径向呈现递增规律，雾化最好的区域分布在雾场中心和两侧。SMD随节流水平增加而增大。当动量比不变时，节流水平对SMD的分布范围影响很小。针栓头部下方的中心回流区轴向尺寸随着节流水平降低而减小。

Abstract

In order to analyze the spray characteristics and spray mechanism of gas⁃liquid pintle injector unit，the effects of throttling level on spray pattern，volume flow rate distribution，Sauter mean diameter （SMD） distribution and the velocity field were obtained by using backing⁃lighting photography technique and phase Doppler anemometry （PDA） system for the spray characteristics of gas⁃liquid pintle injector unit.The results showed that the spray of gas⁃liquid pintle injector was a fan⁃shaped form and the spray pattern was presented by shearing breaking.The volume flow rate presented a single peak distribution along the radial direction.With the decrease of throttling level，the edge of spray field shrank to the center.The SMD increased along the radial direction，and the best spay area was distributed in the center and both sides of the spay field.The value of SMD increased with the increasing throttling level.When the momentum ratio was constant，the throttling level had little influence on the variation range of SMD.The axial length of the backflow area below the pintle head decreased with the decreasing throttling level.

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references

DRELLSER G A , BAUER J M . TRW pintle engine heritage and performance characteristics [R].AIAA 2000 ⁃3871 , 2000 .

刘昌波 , 兰晓辉 , 李福云 , 等 . 载人登月舱下降发动机技术研究 [J]. 火箭推进 , 2011 , 37 （ 2 ）: 8 ⁃ 13 .

LIU Changbo , LAN Xiaohui , LI Fuyun , et al . Conceptual schemes of China lunar excursion module descent engine [J]. Journal of Rocket Propulsion , 2011 , 37 （ 2 ）: 8 ⁃ 13 . （in Chinese）

雷娟萍 , 兰晓辉 , 章荣军 , 等 . 嫦娥三号探测器7 500 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 7 500 N variable thrust engine for Chang'E⁃3 [J]. Science in China Series E（Technological Sciences） , 2014 , 44 （ 6 ）: 569 ⁃ 575 . （in Chinese）

王丹 , 陈宏玉 , 周晨初 . 电动泵压式发动机系统方案与性能评估 [J]. 火箭推进 , 2018 , 44 （ 2 ）: 28 ⁃ 32 .

WANG Dan , CHEN Hongyu , ZHOU Chenchu . Design of single⁃component balance for small thrust measure⁃ment of attitude control engine [J]. Journal of Rocket Propulsion , 2018 , 44 （ 2 ）: 28 ⁃ 32 . （in Chinese）

沈文金 , 叶小强 . 深度变推发动机浮动环工作适应性研究 [J]. 火箭推进 , 2017 , 43 （ 5 ）: 28 ⁃ 33 .

SHEN Wenjin , YE Xiaoqiang . Investigation for working adaptability of floating ring seals in deep throttling en⁃gines [J]. Journal of Rocket Propulsion , 2017 , 43 （ 5 ）: 28 ⁃ 33 . （in Chinese）

王凯，雷凡培，张波涛，等．针栓式喷注单元雾化角模型分析研究 [J]. 航空学报 , 2020 , 41 （ 10 ）: 123622.1 ⁃ 123622.15 .

WANG Kai , LEI Fanpei , ZHANG Botao , et al . Study on spray angle model of pintle injector element [J]. Acta Aeronautica et Astronautica Sinica , 2020 , 41 （ 10 ）: 123622.1 ⁃ 123622.15 . （in Chinese）

BLAKELY J , FREEBERG J , HOGEE J . Spray cone formulation from pintle⁃type injecotr systems in liquid rocket engines [R].AIAA 2019 ⁃0152 , 2019 .

BOETTCHER P A , DAMAZO J S , SHEPHERD J E , et al . Visualization of tranverse annular jets [R]. Minneapolis,US : the 62nd Annual Meeting of the APS Division of Fluid Dynamic , 2009 .

SON M , YU K , KOO J , et al . Effect of momentum ration and weber number on spray half angles of liquid controlled pintle injector [J]. Journal of Thermal Science , 2015 , 24 （ 1 ）: 37 ‑ 43 .

张波涛 , 李平 , 王凯 , 等 . 针栓喷注器中心推进剂偏转角模型分析研究 [J]. 推进技术 , 2021 , 42 （ 7 ）: 1534 ⁃ 1543 .

ZHANG Botao , LI Ping , WANG Kai , et al . Study on central propellant deflection angle model of pintle injector [J]. Journal of Propulsion Technology , 2021 , 42 （ 7 ）: 1534 ⁃ 1543 . （in Chinese）

张波涛 , 李平 , 杨宝娥 . 气液针栓喷注器在节流水平下的雾化角模型分析 [J]. 宇航学报 , 2021 , 42 （ 2 ）: 249 ⁃ 258 .

ZHANG Botao , LI Ping , YANG Baoe , et al . Study on spray angle model of gas⁃liquid pintle injector at throttling level [J]. Journal of Astronautics , 2021 , 42 （ 2 ）: 249 ⁃ 258 . （in Chinese）

王凯 , 雷凡培 , 杨岸龙 , 等 . 针栓式喷注单元膜束撞击雾化混合过程数值模拟 [J]. 航空学报 , 2020 , 41 （ 9 ）: 123802.1 ⁃ 123802.15 .

WANG Kai , LEI Fanpei , YANG Anlong , et al . Numerical simulation on spray and mixing process of impingement between sheet and jet in pintle injector element [J]. Journal of Aerospace Power , 2020 , 41 （ 9 ）: 123802.1 ⁃ 123802.15 . （in Chinese）

FANG X X , SHEN C B . Study on atomization and com⁃bustion characteristics of LOx/methane pintle injectors [J]. Acta Astronautica , 2017 , 136 : 369 ⁃ 379 .

王凯 , 雷凡培 , 杨岸龙 , 等 . 针栓式喷注器液膜下漏率预估模型 [J]. 航空动力学报 , 2020 , 35 （ 10 ）: 2223 ⁃ 2234 .

WANG Kai , LEI Fanpei , YANG Anlong , et al . Prediction model of leakage rate of liquid sheet in pintle injector [J]. Journal of Aerospace Power , 2020 , 35 （ 10 ）: 2223 ⁃ 2234 . （in Chinese）

成鹏 . 变推力火箭发动机喷雾燃烧动态过程研究 [D]. 长沙 : 国防科技大学 , 2018 .

CHENG Peng . The dynamics of spray combustion in variable thrust rocket engines [D]. Changsha : National University of Defense Technology , 2018 . （in Chinese）

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 ）: 204704.1 ⁃ 204704.14 .

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 ）: 204704.1 ⁃ 204704.14 . （in Chinese）

张紫豪 . 可调针栓喷注器喷雾特性试验研究 [D]. 长沙 : 国防科技大学 , 2018 .

ZHANG Zihao . Experimental investigation on the spray characteristics of variable pintle injectors candidate [D]. Changsha : National University of Defense Technology , 2018 . （in Chinese）

方昕昕 , 沈赤兵 , 张新桥 . 针栓式喷注器锥形液膜破碎特性试验 [J]. 航空动力学报 , 2016 , 31 （ 12 ）: 3004 ⁃ 3009 .

FANG Xinxin , SHEN Chibing , ZHANG Xinqiao . Experi⁃ment of breakup characteristics on conical sheets of pintle injectors [J]. Journal of Aerospace Power , 2016 , 31 （ 12 ）: 3004 ⁃ 3009 . （in Chinese）

方昕昕 , 沈赤兵 , 成鹏 , 等 . 针栓式喷注器雾化特性试验 [J]. 航空动力学报 , 2017 , 32 （ 8 ）: 1854 ⁃ 1860 .

FANG Xinxin , SHEN Chibing , CHENG Peng , et al . Experiment on atomization characteristics of pintle injector [J]. Journal of Aerospace Power , 2017 , 32 （ 8 ）: 1854 ⁃ 1860 . （in Chinese）

SON M , YU K , RADHAKRISHNAN K , et al . Verification on spray simulation of a pintle injector for liquid rocket engine [J]. Journal of Thermal Science , 2016 , 25 （ 1 ）: 90 ‑ 96 .

石璞 , 朱国强 , 李进贤 , 等 . 液体火箭发动机针栓喷注器雾化燃烧技术研究进展 [J]. 火箭推进 , 2020 , 46 （ 4 ）: 1 ⁃ 13 .

SHI Pu , ZHU Guoqiang , LI Jinxian , et al . Advances in atom]ized combustion technology research of pintle injector for liquid rocket engines [J]. Journal of Rocket Propulsion , 2020 , 46 （ 4 ）: 1 ⁃ 13 . （in Chinese）

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 . （in Chinese）

沈熊 . 激光多普勒测速技术及应用 [M]. 北京 : 清华大学出版社 , 2004 .

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