|Table of Contents|

Effect of structural parameters of gas-gas coaxial direct-flow injector on combustion performance(PDF)

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

Issue:
2022年03期
Page:
32-39
Research Field:
研究与设计
Publishing date:

Info

Title:
Effect of structural parameters of gas-gas coaxial direct-flow injector on combustion performance
Author(s):
WANG Zhuang;  HU Jinhua;  YANG Jianwen;  JIN Dan;  LI Yandong;  HUO Shihui
(Science and Technology on Liquid Rocket Engine Laboratory, Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
gas-gas coaxial direct-flow injector structural parameters combustion efficiency flame length
PACS:
V434
DOI:
-
Abstract:
Gas-gas coaxial direct-flow injector is widely used in the full-flow staged combustion cycle rocket engine, and the structural parameters of the injector affect the performance of the main thrust chamber.In order to explore the influence of the structural parameters of the gas-gas coaxial direct-flow injector on the combustion performance, four structural parameters are analyzed through numerical calculation, which include the diameter of the oxygen nozzle, the width of the fuel nozzle, the wall thickness between the fuel nozzle and the oxygen nozzle, and the indent distance of the central nozzle.The results show that the diameter of oxygen nozzle and the wall thickness between fuel nozzle and oxygen nozzle have significant influence on the flame length, while the width of fuel nozzle and the indent distance have little effect on the flame length.As the diameter of oxygen nozzle and the wall thickness increase, the flame length increases and the combustion efficiency decreases.In addition, the width and indent distance of fuel nozzle have a great influence on the mixing of the propellant components.A certain indent distance can enhance the mixing of components and improve the flame stability.

References:

[1] 金平,蔡国飙.全流量补燃循环发动机及其特点[J].火箭推进,2003,29(4):43-47.
JIN P,CAI G B.FFSC engine and its characteristics[J].Journal of Rocket Propulsion,2003,29(4):43-47.
[2] 孙宏明.直流式喷注器设计[J].火箭推进,2004,30(5):1-9.
SUN H M.Design of orifice injector[J].Journal of Rocket Propulsion,2004,30(5):1-9.
[3] 杜正刚,高玉闪,蔡国飙.气-气喷嘴结构分析[J].火箭推进,2009,35(3):6-10.
DU Z G,GAO Y S,CAI G B.Structure pattern analysis of gas-gas injector[J].Journal of Rocket Propulsion,2009,35(3):6-10.
[4] PASTER R D.Hydrogen-oxygen APS engines[R].NASACR-120805,1973.
[5] Aerojet Liquid Rocket Company.Stability characterization of advanced injectors[R].20672-P3F,1971.
[6] MUENKER A H.Advanced maneuvering propulsion technology program[R].AFRPL-TR-76-05,1976.
[7] CALHOON D,ITO J I,KORS D.Investigation of gaseous propellant combustion and associated injector-chamber design guidelines[R].NASA CR-121234,1973.
[8] FARHANGI S,YU T,ROJAS L,et al.Gas-gas injector technology for full flow stage combustion cycle application[C]//35th Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1999.
[9] 金平,杜正刚,杨立军,等.气-气喷注器混合场流动显示[J].航空动力学报,2011,26(1):210-216.
[10] 金平,杜正刚,杨立军,等.同轴式气-气喷注器混合场影响因素流动显示研究[J].航空动力学报,2011,26(3):692-697.
[11] 李茂,高玉闪,金平,等.富氢/富氧燃气气-气喷嘴热试[J].推进技术,2010,31(6):696-700.
[12] WANG X W,CAI G B,GAO Y S.Scaling of heat transfer in gas-gas injector combustor[J].Chinese Physics B,2011,20(6):064701.
[13] 杜正刚,李茂,金平,等.大流量气-气喷嘴响应面法优化设计[J].北京航空航天大学学报,2010,36(4):395-398.
[14] 杜正刚,高玉闪,李茂,等.同轴双剪切气-气喷嘴数值模拟[J].航空动力学报,2010,25(4):829-834.
[15] 杜正刚,高玉闪,李茂,等.同轴双剪切气-气喷嘴试验研究[J].推进技术,2010,31(2):170-173.
[16] WANG X W,CAI G B,GAO Y S,et al.Large flow rate shear-coaxial gas-gas injector[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2009.
[17] 汪小卫,高玉闪,金平,等.气气多喷嘴推力室仿真与试验研究[J].推进技术,2011,32(1):80-85.
[18] WILCOX D C.Turbulence modeling for CFD[M].La Canada,California:DCW Industries Inc,1998.
[19] RIECHELMANN D,KATO S,FUJIMORI T.Effect of presumed PDF selection on the numerical result for turbulent diffusion flames[J].JSME International Journal Series B,2002,45(1):108-111.
[20] BATT R G.Turbulent mixing of passive and chemically reacting species in a low-speed shear layer[J].Journal of Fluid Mechanics,1977,82(1):53-95.
[21] MUNGAL M G,DIMOTAKIS P E.Mixing and combustion with low heat release in a turbulent shear layer[J].Journal of Fluid Mechanics,1984,148:349-382.
[22] ESWARAN V,POPE S B.Direct numerical simulations of the turbulent mixing of a passive scalar[J].The Physics of Fluids,1988,31(3):506-520.
[23] 张会强,周力行,林文漪,等.湍流扩散燃烧多点δ-PDF模型[J].燃烧科学与技术,2000,6(1):57-62.
[24] 曹红军,张会强,林文漪.基于大涡模拟的湍流非预混燃烧混合分数概率密度函数[J].清华大学学报(自然科学版),2012,52(7):1018-1022.
[25] CELANO M P,SILVESTRI S,SCHLIEBEN G,et al.Injector characterization for a gaseous oxygen-methane single element combustion chamber[J].Progess in Propulsion Physics,2016,8:145-164.

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