|Table of Contents|

Effects of structural parameters on the spray characteristics of variable pintle injectors(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2022年05期
Page:
9-17
Research Field:
目次
Publishing date:

Info

Title:
Effects of structural parameters on the spray characteristics of variable pintle injectors
Author(s):
ZHANG Zihao1; 2;  WU Jiping1; 2;  CHENG Peng1; 2;  JIANG Yanping1; 2
(1.College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China 2.Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)
Keywords:
throttling liquid rocket engine pintle injector spray characteristics blockage factor sleeve expansion angle atomization experiments
PACS:
TN95
DOI:
-
Abstract:
To reveal the influence of structural parameters on the spray characteristics of variable pintle injectors, the cold atomization experiments of liquid/liquid pintle injector were carried out by using high-speed photography and Malvern techniques.The effects of geometrical parameters, such as blockage factor and sleeve expansion angle on flow characteristics, spray angle and SMD were analyzed.The experimental results show that the geometrical parameters such as blockage factor and sleeve expansion angle have great influence on the flow coefficient.Under the same momentum ratio, the blockage factor has a significant effect on the spray angle, SMD and spatial distribution of SMD, which may be caused by the change of local momentum ratio.The further downstream the spray goes, the smaller the SMD is.Lager sleeve expansion angle leads to smaller spray angle and lager SMD.When the sleeve expansion angle is less than 90°, SMD will decrease significantly.From the above results, it can be found that at a certain momentum ratio, the proper spray distribution and droplet size were obtained by properly enlarging blockage factor and sleeve expansion angle of oxidant center pintle injector, or decreasing blockage factor and sleeve expansion angle of fuel center pintle injector, to improve the atomization performance.

References:

[1] 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.
[2] DRESSLER G.Summary of deep throttling rocket engines with emphasis on Apollo LMDE[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2006.
[3] HARDGROVE J,KRIEG H.High performance throttling and pulsing rocket engine[C]//20th Joint Propulsion Conference.Reston,Virginia:AIAA,1984.
[4] DRESSLER G,TAO P.Kew divert propulsion technology verfication and risk reduction program[Z].1988.
[5] GROMSKI J,MAJAMAKI A,CHIANESE S,et al.Northrop grumman TR202 LOX/GH2 deep throttling engine project status[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2010.
[6] 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.
[7] 岳春国,李进贤,冯喜平,等.针栓式变推力火箭发动机技术现状与发展探索[J].世界科技研究与发展,2008,30(5):609-612.
[8] 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):1853-1860.
[9] SON M,RADHAKRISHNAN K,KOO J,et al.Design procedure of a movable pintle injector for liquid rocket engines[J].Journal of Propulsion and Power,2016,33(4):858-869.
[10] SON M,YU K,KOO J,et al.Effects of momentum ratio and Weber number on spray half angles of liquid controlled pintle injector[J].Journal of Thermal Science,2015,24(1):37-43.
[11] ZHOU W Y,XU X,YANG Q C,et al.Experimental and numerical investigations on the spray characteristics of liquid-gas pintle injector[J].Aerospace Science and Technology,2022,121:107354.
[12] 龙治光,俞南嘉,蔡国飙,等.液氧/气甲烷针栓喷注器雾化特性数值研究[C]//第六届空天动力联合会议暨中国航天第三专业信息网第四十二届技术交流会暨2021航空发动机技术发展高层论坛论文集(第三册).成都:中国航天第三专业信息网,2022.
[13] LEE S J,KOO J,YOON Y.Effects of skip distance on the spray characteristics of a pintle injector[J].Acta Astronautica,2021,178:471-480.
[14] ZHANG Y,YU N J,TIAN H,et al.Experimental and numerical investigations on flow field characteristics of pintle injector[J].Aerospace Science and Technology,2020,103:105924.
[15] 金烜,沈赤兵,林森,等.数值模拟气液针栓式火箭发动机喷雾燃烧对声学激励的响应[J].国防科技大学学报,2021,43(5):36-45.
[16] CHENG P,LI Q L,CHEN H Y.Flow characteristics of a pintle injector element[J].Acta Astronautica,2019,154:61-66.
[17] NINISH S,VAIDYANATHAN A,NANDAKUMAR K.Spray characteristics of liquid-liquid pintle injector[J].Experimental Thermal and Fluid Science,2018,97:324-340.
[18] SAKAKI K,KAKUDO H,NAKAYA S,et al.Optical measurements of ethanol/liquid oxygen rocket engine combustor with planar pintle injector[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2015.
[19] SAKAKI K,KAKUDO H,NAKAYA S,et al.Performance evaluation of rocket engine combustors using ethanol/liquid oxygen pintle injector[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2016.
[20] 陈慧源,李清廉,成鹏,等.针栓喷注器径向孔形状对喷雾特性影响实验研究[J].推进技术,2022,43(3):209-215.
[21] 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.
[22] SONG W,HWANG J,KOO J.Atomization of gelled kerosene by multi-hole pintle injector for rocket engines[J].Fuel,2021,285:119212.
[23] 曹建明.液体喷雾学[M].北京:北京大学出版社,2013.
[24] 何志勇,孙立宁,陈立国.Otsu准则下分割阈值的快速计算[J].电子学报,2013,41(2):267-272.
[25] MUGELE R A,EVANS H D.Droplet size distribution in sprays[J].Industrial & Engineering Chemistry,1951,43(6):1317-1324.
[26] 孙纪国.氢氧同轴式喷嘴流量特性试验和理论分析[J].航空动力学报,2005,20(4):689-692.
[27] BRUNNO B,HAIDN O.Effect of pintle injector element geometry on combustion in a liquid oxygen/liquid methane rocket engine[C]//7th European Conference for Aeronautics and Aerospace Sciences.Milan:[s.n.],2017.

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Last Update: 1900-01-01