Ignition Process Evolution at High Supersonic Velocities in Channel

作     者：M.A.Goldfeldl A.V.Starov K.Yu.Timofeev V.A.Vinogradov 

作者机构：Institute of Theoretical and Applied Mechanics Central Institute of Aviation Motors 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2009年第18卷第2期

页      面：166-172页

核心收录：

学科分类：080701[工学-工程热物理] 08[工学] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0702[理学-物理学] 

主　　题：supersonic combustor ignition stable combustion. 

摘      要：The results of experimental research of multi-injector combustors in the regime of the attached pipe are *** 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.