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激波风洞中超声速燃烧现象的初步实验研究
引用本文:袁生学,赵伟,黄志澄.激波风洞中超声速燃烧现象的初步实验研究[J].燃烧科学与技术,2001,7(2):149-152.
作者姓名:袁生学  赵伟  黄志澄
作者单位:中国科学院力学研究所
基金项目:国家自然科学基金资助项目(19482010,59686005)。
摘    要:激波风洞可以提供超声速燃烧现象研究需要的高速和高温实验模拟条件,而且在实验时间上优于膨胀管和重活塞风洞,但是由于其技术难度,很少用于超声速燃烧现象研究。文章介绍了启用激波风洞进行燃烧研究所作的改造和得到的初步实验结果。实验除测量常规流场参数和模型表面的动态参数外,主要使用二维实验模型,利用高温气体的自发光和燃烧伴随的发光现象,采用高速摄影技术来观测燃烧现象,记录到高焓流场中叠加燃料喷射和燃烧的流场,观察到自由边界条件下扩控制的超声速燃烧现象。结果表明激波风洞用于超声速燃烧研究的一些必要的技术问题已基本解决。

关 键 词:超声波燃烧  扩散燃烧  激波风洞  流动显示
文章编号:1006-8740(2001)02-0149-04
修稿时间:1999年11月22

Preliminary Experimental Investigation on Supersonic Combustion Phenomena with Shocktunnel
YUAN Sheng-xue,ZHAO Wei,HUANG Zhi-cheng.Preliminary Experimental Investigation on Supersonic Combustion Phenomena with Shocktunnel[J].Journal of Combustion Science and Technology,2001,7(2):149-152.
Authors:YUAN Sheng-xue  ZHAO Wei  HUANG Zhi-cheng
Abstract:A combustion or detonation driven shock tunnel may provide hyper velocity and high temperature for the investigation of supersonic combustion phenomena in a several millisecond period,but few of them have been employed in the world for some technical reasons.This paper introduces the method of investigation on supersonic combustion with a shock tunnel,the experimental setup and preliminary results.In addition to measurements of conventional dynamic parameters on a model surface,an optical observation method was employed,which directly recorded self luminosity of high temperature gas induced by a two dimensional model in high enthalpy flow and combustion radiation.Hypersonic flow fields passing over a sharp strut including fuel injection were displayed and recorded with a high speed CCD camera.A phenomenon of supersonic diffusive combustion under free boundary condition was observed.The results show that some of technological problems for experimental investigation on supersonic combustion with shock tunnels have been solved basically.
Keywords:supersonic combustion  diffusive combustion  shock tunnel  high enthalpy  flow visualization
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