Ignition process evolution at high supersonic velocities in channel

被引：0
|
作者：
M. A. Goldfeld
A. V. Starov
K. Yu. Timofeev
V. A. Vinogradov
机构：
[1] Institute of Theoretical and Applied Mechanics,
[2] Central Institute of Aviation Motors,undefined
来源：
Journal of Thermal Science | 2009年 / 18卷
关键词：
supersonic combustor; ignition; stable combustion;
D O I：
暂无
中图分类号：
学科分类号：
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 of the Russian Academy of Sciences was used. Tests have been carried out at Mach numbers 3, 4 and 5, in a range of change of total temperature from 2000K up to 3000K and static pressure from 0.08MPa up to 0.23MPa. Injector section has been manufactured in two versions with a various relative height of wedge-shaped injectors with parallel fuel injection. Influence of conditions on the entrance of the combustion chamber on ignition and a stable combustion of hydrogen was investigated. Intensive combustion of hydrogen has been received only at Mach numbers 3 and 4. Advantage of injector section with the greater relative height of injectors is revealed. The mechanism of fuel ignition in the combustion chamber of the given configuration was investigated: two-step ignition process including “kindling” and intensive combustion over all channel volume.
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页码：166 / 172
页数：6
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