文章基本信息

标题：Computational Analysis for Investigating the Effects of Circular Cavity in a Supersonic Combustor
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作者：Ajay Sampath H A ; N Chikkanna
期刊名称：International Journal of Innovative Research in Science, Engineering and Technology
印刷版ISSN：2347-6710
电子版ISSN：2319-8753
出版年度：2018
卷号：7
期号：8
页码：9132-9142
DOI：10.15680/IJIRSET.2018.0708034
出版社：S&S Publications
摘要：The computation aims at studying the effects of circular cavity in its different flow regimes i.e. open, closed and transitional flows depending on the L/D of the cavity and compared with its computed rectangular cavity counter parts. Since there has not been many research in circular cavity, the closely related cavity i.e. rectangular cavity is used for comparison. The flow has been computed for an inlet Mach number of 3 and a stagnation pressure of 6.9bar, the L/D ratios used are 5.5 open flow, 10 transitional flow and 13 closed flow. This study also includes a computation on fuel injection at a distance of 8 mm from cavity, the fuel is injected from an injecting surface of 1mm with a total pressure of 14bar. This further aids in understanding the fuel mixing for all variant of cavities. An attempt is made to provide some guidelines for the future research of circular cavity flame holders. The study concludes thatas we increase the L/D ratio, the cavity effect diminishes in closed and transitional flows for circular cavity and in closed flow for rectangular cavity. The flow requirement such as not having the generation of series of compression waves in the higher L/D and detachment of compression waves at the aft wall is seen in the circular cavity. The fuel distribution is promising in open flow for circular cavity, the fuel distribution in rectangular cavity is promising in open and transitional flows.
关键词：Supersonic combustion; Cavity; L;D ratio; Mach; Combustor; Pressure gradient