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等截面引射器启动性能数值研究 被引量:7

Numerical investigation on starting performance of constant-area ejector
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摘要 采用雷诺平均方程和SST k-ω湍流模型,空间离散采用二阶精度的Roe FDS方法,限制器采用Min-Mod方法,时间迭代采用隐式方法,研究了等截面引射器长度、引射器与喷管的间隙对其启动性能的影响。结果表明:等截面引射器存在启动、临界、不启动三种状态;在引射器长度一定的情况下,引射器与喷管之间的间隙越小,引射器的启动压比越小;在引射器与喷管之间间隙一定的情况下,对于本文所计算的工况,当引射器长度小于3m时,引射器所需的启动压比会很大,当引射器长度小于2m,则引射器很难启动;当引射器长度超过7m时,会对引射器的加工、安装、冷却带来诸多不利影响。 In order to investigate how the geometry parameters influence the starting performance in constant-area ejector, by using Reynolds averaged equations and SST k-ω turbulence model, the numerical simulation of constant-area ejector flow field is made in this paper. The Roe FDS method with second-order accuracy is adopted for spatial discretization, the Min-Mod method is applied to the limiter, the implicit method is used for time iteration. Results suggest that constant-area ejector has starting, critical and un-starting three modes. When the ejector length is a constant-parameter, the critical starting pressure ratio is increased by increasing the distance of diffuser to nozzle exit, when the distance of diffuser to nozzle exit is kept at constant, if the ejector length is too short, the critical starting pressure ratio will be too high even the ejector will be hard to start. When the ejector length is too long, the adverse effects on the processing, installation and cooling of ejector will occur.
出处 《应用力学学报》 CAS CSCD 北大核心 2014年第5期697-702,828,共7页 Chinese Journal of Applied Mechanics
关键词 等截面引射器 喷管 启动性能 数值研究 constant-area ejector,nozzle starting performance,numerical simulation
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  • 1贺军科,吴雄.被动式引射器内流场数值研究[J].固体火箭技术,2005,28(2):116-119. 被引量:6
  • 2Wang J J, Chen F. On the start condition of a secondthroat ejector-diffuser [ J ]. Aeronautical Journal, 1996, 100(998). 被引量:1
  • 3Desevaux P, Lanzetta F. Computational fluid dynamic modeling of pseudo-shock inside a zero-secondary flow ejector [J]. AIAA Journal, 2004, 42(7). 被引量:1
  • 4Desevaux P, Marynowski T, Khan M. CFD prediction of supersonic ejectors performance [ J ]. International Journal of Turbo & Jet-Engines, 2006, 23 ( 3 ). 被引量:1
  • 5Ginoux J J. Supersonic ejector [ R]. AGARD-AG-163, 1972. 被引量:1
  • 6Falin Chen, Liu C F, Yang J Y. Supersonic flow in the second-throat ejector-diffuser system [ J ]. Journal of Spacecraft and Rockets, 1994, 31 ( 1 ). 被引量:1
  • 7Hiroshi Miyajima, Kazuo Kusaka, Yukio Kuroda, et al. Effects of subsonic diffuser and nozzle contour on the performance of zero-secondary-flow ejector [ R ]. NAL TR- 493, 1977. 被引量:1
  • 8Bauer R C, German R. The effect of secod throat geometry on the performance of ejectors without induced flow [ R ]. AEDC-TN-612133. 被引量:1
  • 9Jones W L, Frice H G, Lorenzo C F. Experimental study of zero-flow ejectors using gasous nitrogen [ R ]. NASA TN D- 203. 被引量:1
  • 10Byung Hoon Park, Ji Hwan Lira, Woongsup Yoon. Fluid dynamics in starting and terminating transients of zero-secondary flow ejector[J]. Int. J. Heat and Fluid Flow,2007: 1-13. 被引量:1

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