多喷嘴大流量气 -气喷注器设计与试验

汪小卫; 高玉闪; 蔡国飙

多喷嘴大流量气 -气喷注器设计与试验

北京航空航天大学宇航学院, 北京 100191

基金项目: 国家高技术研究发展计划(2008AA702^*)

计量
- 文章访问数: 2084
- HTML浏览量: 170
- PDF量: 20
- 被引次数: 0
出版历程
- 收稿日期: 2010-11-28
- 修回日期: 2011-02-24
- 刊出日期: 2011-10-28

Design and experimental study on high flowrate multi-element gas-gas injector chamber

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 在大流量气-气喷注器单喷嘴工况研究的基础上,为研究其在具有单元交互作用的多喷嘴工况下的燃烧特性,设计了多喷嘴推力室.喷注单元为剪切混合式单元,并具有高氢/氧速度比和氧喷嘴扩口设计,采用了能够模拟真实发动机工况的7单元同心圆排布的推力室头部结构,在对喷注单元的排布间距优化设计基础上,开展了热试车试验研究和仿真分析.结果表明所设计的喷注器在多喷嘴工况下燃烧稳定,能够在额定参数设计的燃烧室内,在SSME(space shuttle main engine)主喷注单元流量的3.7倍大流量工况下燃烧效率达到99%以上,并显示出良好的喷注器自身和带来的燃烧室身部热防护特性.
- 气气燃烧 /
- 大流量 /
- 多喷嘴 /
- 全流量补燃循环 /
- 优化设计
Abstract: To investigate the combustion characteristics of high flowrate injector in the multi-element injector chambers having interaction between the elements,based on high flowrate gas-gas injector studies in the single-element condition,a multi-element injector equipped with seven shear mixing elements was deigned,which can simulate effectively the real engine.The shear mixing element had high H₂/O₂ velocity ratio and tapered O₂ post tip.Numerical simulation and hot-fire tests were carried out with this injector using the optimal design of the injector layout.Steady operations were obtained in all these tests,and the injector showed benign heat environments on the faceplates and cylinder walls.Combustion efficiency above 99% was gotten for this injection element in the flowrate of 3.7 times of SSME(space shuttle main engine) main injection element.
- gas gas combustion /
- high flowrate /
- multi-element /
- full flow staged combustion cycle(FFSC) /
- optimization design

HTML

参考文献(17)

[1]	Davis J A,Campbell R L.Advantages of a full-flow staged combustion cycle engine system .AIAA 1997-3318,1997.
[2]	Tucker P K,Klemt M D,Smith T D.Design of efficient gO₂/gH₂,injectors a NASA,industry and university cooperative effort .AIAA 1997-3350,1997.
[3]	Farhangi S,Yu T,Rojas L,et al.Gas-gas injector technology for full flow stage combustion cycle application .AIAA 1999-2757,1999.
[4]	Smith T D,Kevin M K,Breisacher J.Experimental evaluation of a subscale gaseous hydrogen/gaseous oxygen coaxial rocket injector .NASA/TM-2002-211982,2002.
[5]	William M M,Sibtosh P,Woodward R D,et al.Benchmark wall heat flux data for a gO₂/gH₂ single element combustor .AIAA 2005-3572,2005.
[6]	Conley A,Vaidyanathan A,Segal C.Heat flux measurements for a gO₂/gH₂ single-element,shear injector[J].Journal of Spacecraft and Rockets,2007,44(3):633-639.
[7]	Lin J,West J S,Williamst R W,et al.CFD code validation of wall heat fluxes for a gO₂/gH₂ single element combustor .AIAA 2005-4524,2005.
[8]	Calhoon D,Ito J,Kors D.Investigation of gaseous propellant combustion and associated injector chamber design guide-lines .Aerojet Liquid Rocket Company,NASA CR-121234,Contract NAS3-13379,1973.
[9]	Groot W,Mcguire T J,Schneider S J.Qualitative flow visualization of a 110N hydrogen/oxygen laboratory model thruster .AIAA 1997-2847,1997.
[10]	Tamura H,Sakamoto H,Takahashi M,et al.LOX/LH₂ subscale swirl coaxial injector testing .AIAA Paper 1997-2906,1997.
[11]	Fujita M,Fukushima Y.Improvement of LE-5A and LE-7 engine .AIAA 1996-2847,1996.
[12]	Haeseler D,Mading C,Preclik D.LOX-kerosene oxidizer-rich gas-generator and main combustion chambers subscale testing .AIAA 2006-5197,2006.
[13]	汪小卫,金平,高玉闪,等.单喷嘴大流量气-气喷注器设计与试验[J].航空动力学报,2010,25(3):691-698. WANG Xiaowei,JIN Ping,GAO Yushan,et al.Design and experiment of high flowrate single-element gas-gas injectors[J].Journal of Aerospace Power,2010,25(3):691-698.(in Chinese)
[14]	汪小卫,金平,杜正刚,等.氢/氧气-气喷注器冷流掺混与燃烧比较的仿真研究[J].航空动力学报,2008,23(9):1737-1742. WANG Xiaowei,JIN Ping,DU Zhenggang,et al.Simulation of cold flow and combustion characteristics of shear-coaxial GH₂/GO₂ injectors[J].Journal of Aerospace Power,2008,23(9):1737-1742.(in Chinese)
[15]	汪小卫,金平,蔡国飙.一种研究单喷嘴燃烧内流场的方法[J].北京航空航天大学学报,2009,35(9):1095-1099. WANG Xiaowei,JIN Ping,CAI Guobiao.Method for investigation of combustion flowfield characteristics in single-element gas/gas injector chamber[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(9):1095-1099.(in Chinese)
[16]	Sozer E,Vaidyanathan A,Segal C,et al.Computational assessment of gaseous reacting flows in single element injector .AIAA 2009-449,2009.
[17]	邱轶兵.试验设计与数据处理[M].合肥:中国科学技术大学出版社,2008.