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同轴撞击气-气喷嘴数值模拟和实验 被引量:1

Experiment and simulation of impinging coaxial gas-gas injector
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摘要 为进一步深入研究喷嘴结构参数对气-气掺混燃烧特性的影响,针对氢向氧斜喷带撞击角度的气-气喷嘴开展了实验和数值模拟.实验研究了撞击角度对燃烧效率和燃烧室壁面温度的影响,数值仿真分析了撞击角度对喷注面板和氧喷嘴管壁温的影响.结果表明:随着氢向氧撞击角度的增大,推进剂燃烧效率、燃烧室壁面和氧喷嘴出口管壁面热载降低;氢向氧撞击角度的引入,增大了喷注面板热载. In order to investigate the effect of design parameters of gas-gas injector on mixing and combustion characteristics,experiment and numerical simulation were conducted on the injectors which had an angle that gaseous hydrogen impinge gaseous oxygen.Hot fire tests were carried out to investigate the effect of impinging angle on the combustion efficiency and the chamber wall temperature.Numerical simulation was performed to analysis the effect of the impinging angle on the temperature of the injector faceplate and the oxygen post tip.The results show that the combustion efficiency,the thermal load of the chamber wall and the oxygen post tip decrease as the impinging angle increases;the impinging angle of the gaseous hydrogen towards gaseous oxygen makes the thermal load of the injector faceplate increases.
出处 《北京航空航天大学学报》 EI CAS CSCD 北大核心 2011年第8期923-926,共4页 Journal of Beijing University of Aeronautics and Astronautics
基金 国家863计划资助项目(2009AA7020504)
关键词 气-气喷嘴 撞击角 燃烧效率 热载 gas-gas injector impinging angle combustion efficiency thermal load
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参考文献11

  • 1Farhangi S, Yu T, Rojas L, et al. Gas-Gas injector technology for full flow combustion cycle application [ R ]. AIAA-1999-2757, 1999.
  • 2Foust M J,pal S,Santoro R J. Gaseous propellant rocket studies using raman spectroscopy [ R ]. AIAA - 1996-2766,1996.
  • 3Archambauh M R, Talley D, Peroomian O. Computational analy- sis of a single-element, shear-coaxial, GH2/G02 engine [ R ]. AIAA -2002-1088,2002.
  • 4Vaidyanathan A, Gustavsson J, Segal C. Heat fluxes/OH PLIF measurements in a GO2/GH2 single-element, shear injector [ R ]. AIAA-2007-5591 , 2007.
  • 5Wang Xiaowei,Cai Guobiao,Jin Ping. Scaling of the flowfield in a combustion chamber with a gas-gas injector[J]. Chin Phys B, 2010,19(1) :345 -352.
  • 6杜正刚,高玉闪,蔡国飙.氧压降对气-气喷注器燃烧过程的影响[J].宇航学报,2009,30(2):675-679. 被引量:1
  • 7杜正刚,高玉闪,金平,蔡国飙.速度比对气-气喷嘴燃烧性能的影响[J].推进技术,2009,30(5):551-554. 被引量:7
  • 8Vaidyanathan R,Tucker P K, Papila N, et al. CFD-based design optimization for a single element rocket injector [ R ]. AIAA- 2003 -296,2003.
  • 9Vaidyanathan R, Tucker P K, Papila N, et al. Computational-flu- id-dynamics-based design optimization for single-element rocket injector[ J ]. Journal of Propulsion and Power, 2004,20 ( 4 ) : 705 -717.
  • 10Vaidyanathan R, Goel T, Shyy W, et al. Global sensitivity and trade-off analyses for multi-objective liquid rocket injector de- sign [ R ]. AIAA-2004-4007,2004.

二级参考文献9

  • 1Farhangi S, Yu T, Rojas L, et al. Gas-Gas Injector Technology for Full Flow Combustion Cycle Application [ R ]. A1AA 99 - 2757.
  • 2Calhoon D, Ito J, Kors D. Investigation of Gaseous Propellant Combustion and Associated Injector-Chamber Design Guidelines [ R]. NASA CR-121234, Contract NAS3-13379, July 1973.
  • 3Foust M J, pal S, Santoro R J. Gaseous Propellant Rocket Studies Using Raman Spectroscopy[ R ]. AIAA 96 -2766.
  • 4Jones R A, Groot W A. Oxygen Temperature and Concentration Measurements in H2-O2 , Rocket Engines[ R ] A1AA 96 -0439.
  • 5Foust M J, Deshpande M, Pal S. Experimental and Analytical Characterization of A Shear Coaxial Combusting GO2/GH2 Flowfield [ R ]. AIAA 96 - 0646.
  • 6Conley A, Vaidyanathan R, Segal C. Heat flux measurements for a GO2/GH2 single-element shear injector[ J]. Journal of Propulsion and Power, 2007, 44 (3) : 633 -639.
  • 7Vaidyanathan R, Tucker P K, Papila N. Computational-fluid-dynamics-based design optimization for single-element rocket injector[J]. Journal of Propulsion and Power 2004, 20(4) : 705 -717.
  • 8Shang H M, Chen Y S, Liaw P. Investigation of Chemical Kinetics Integration Algorithms for Reacting Flows[ R]. A1AA 95 -0506.
  • 9萨顿GP 比布拉兹O.火箭发动机基础[M].北京:科学出版社,2003..

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