Ignition Process Evolution at High Supersonic Velocities in Channel

被引：0
|
作者：
M.A.Goldfeldl [1 ]
A.V.Starov [1 ]
K.Yu.Timofeev [1 ]
V.A.Vinogradov [2 ]
机构：
[1] Institute of Theoretical and Applied Mechanics
[2] Central Institute of Aviation Motors
来源：
Journal of Thermal Science | 2009年 / 18卷 / 02期
关键词：
supersonic combustor; ignition; stable combustion;
D O I：
暂无
中图分类号：
TK121 [工程热物理学];
学科分类号：
080701 ;
摘要：
The results of experimental research of multi-injector combustors in the regime of the attached pipe are presented.As a source of high-enthalpy working gas (air), hot shot wind tunnel IT-302M of ITAM, the Siberian Branch ofthe Russian Academy of Sciences was used. Tests have been carried out at Mach numbers 3,4 and 5, in a range ofchange of total temperature from 2000K up to 3000K and static pressure from 0.08MPa up to 0.23MPa. Injectorsection has been manufactured in two versions with a various relative height of wedge-shaped injectors with parallelfuel injection. Influence of conditions on the entrance of the combustion chamber on ignition and a stablecombustion of hydrogen was investigated. Intensive combustion of hydrogen has been received only at Machnumbers 3 and 4. Advantage of injector section with the greater relative height of injectors is revealed. Themechanism of fuel ignition in the combustion chamber of the given configuration was investigated: two-step ignitionprocess including "kindling" and intensive combustion over all channel volume.
引用
收藏
页码：166 / 172
页数：7
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