Ignition and combustion of hydrogen in a channel with high supersonic flow velocities at the channel entrance

被引：0
|
作者：
V. A. Vinogradov
M. A. Goldfeld
A. V. Starov
机构：
[1] Central Institute of Aviation Motors,Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch
[2] Russian Academy of Sciences,undefined
来源：
Combustion, Explosion, and Shock Waves | 2013年 / 49卷
关键词：
supersonic velocity; combustor; hydrogen;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
Results of experimental investigations of a multi-injector combustion chamber in the attached pipeline regime are presented. An IT-302M hotshot wind tunnel based at the Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences is used as a source of a high-enthalpy gas (air). The tests are performed at Mach numbers of 3, 4, and 5 in the ranges of the total temperature from 2000 to 3000 K and static pressure from 0.08 to 0.23 MPa. The block of injectors is made in two variants: with different relative lengths of wedge-shaped injectors (cocurrent injection of hydrogen). The influence of the conditions at the combustor entrance on ignition and stable combustion of hydrogen is studied. Intense combustion of hydrogen is obtained only at Mach numbers of 3 and 4. The mechanism of the “two-stage” evolution of fuel combustion in the combustor is analyzed. The experimental data are analyzed and compared with numerical predictions.
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页码：383 / 391
页数：8
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