Numerical simulation of dual shear coaxial gas-gas injector
-
摘要: 通过求解 k-ε 湍流模型的Navier-Stokes 方程组,对以气氢/气氧为推进剂的同轴双剪切喷嘴燃烧室进行数值模拟研究.研究结果表明:与传统的同轴剪切喷嘴相比,双剪切气-气喷嘴使推进剂有两个剪切燃烧面,且出口尺寸变化不大;双剪切喷嘴中心氢与氢总质量流量的比例是双剪切喷嘴的关键设计参数,当比例值为0.3时,能充分发挥双剪切喷嘴两个燃烧面的优势,使双剪切喷嘴能在大流量工况下实现高的燃烧效率.
-
关键词:
- 数值模拟 /
- Navier-Stokes方程组 /
- 效率
Abstract: The turbulent Navier-Stokes equations in combination with the two equation k-ε turbulence model were used to simulate the flowfield in chambers of dual shear coaxial injector which the gaseous oxygen and hydrogen were used as propellants. The results of investigation display that: compared with traditional shear coaxial injector, the dual shear coaxial injector creates two shear combustion faces in chamber, and its outline varies a small amount. The ratio of center hydrogen mass flowrate to the total hydrogen mass flowrate is a key parameter for dual shear coaxial injector; at the ratio of 0.3, the advantage of two combustion surfaces is exerted completely. The dual shear coaxial injector could achieve a high combustion efficiency at the condition of large mass flowrate.-
Key words:
- numerical simulation /
- Navier-Stokes equations /
- efficiency
-
[1] Calhoon D, Ito J, Kors D. Investigation of gaseous propellant combustion and associated injector chamber design guidelines .NASA CR-121234,1973 [2] Foust M, pal S, Santoro R.Gaseous propellant rocket studies using raman spectorscopy . AlAA-1996-2766, 1996 [3] Jones A,Groot W. Oxygen temperature and concentration measurements in H2-O2 rocket engines . AIAA-1996-0439, 1996 [4] Foust M, Deshpande M, Pal S.Experimental and analytical characterization of a shear coaxial combusting GO2/G2 flowfield . AlAA-1996-0646, 1996 [5] Jacques B, Martin S. Tricoaxial injector technology development . AlAA-1999-2492,1999 [6] Fournet A,Lonchard J,Thomas J. Technological demonstration for low cost gas generator . AIAA-2004-4006, 2004 [7] 程圣清,宋连忠,王珏.氢氧火箭发动机预燃室喷注器特性研究[J].导弹与航天运载技术,1998,5(1):6-15 Cheng Shengqing,Song Lianzhong,Wang Jue.The study of preburner injector character istics for the hydrogen-oxygen engine[J].Missiles and Space Vehicles, 1998, 5(1):6-15(in Chinese) [8] 中国航天工业总公司.世界导弹与航天发动机大全[M].北京:军事科学出版社, 1999:116 China Aerospace Science and Industry Corporation. An encyclopedia of world missile and space engine[M]. Beijing: Military Science Press, 1999:116(in Chinese) [9] Shang M, Chen Y, Paul L. Investigation of chemical kenetics integration algorithms for reacting flows . AIAA-1995-0806, 1995 -
点击查看大图
计量
- 文章访问数: 3509
- HTML全文浏览量: 187
- PDF下载量: 1016
- 被引次数: 0
下载:
