...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Aerospace science and technology >Combustion enhancement via tandem cavities within a Mach 8 scramjet combustor
【24h】

Combustion enhancement via tandem cavities within a Mach 8 scramjet combustor

机译：Combustion enhancement via tandem cavities within a Mach 8 scramjet combustor

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相关主题

摘要

This paper presents a fundamental numerical investigation of an ethylene fuelled axisymmetric scramjet using single and tandem cavity flameholders. A scramjet profile was designed comprising a truncated Busemann diffuser, isolator, and a constant-to-divergent area combustor. Flight equivalent, Mach 8 flow was delivered to four combustor variants equipped with a single or one of three tandem cavities. Two tandem cavity pairs were positioned within the constant-area combustor, and the remaining was located at the combustor's diverging portion. Fuelling rates of 25%, 50% and 75% of stoichiometric fuel/air ratios were considered. Combustor performance was assessed on mixing and combustion efficiencies, heat release, and total drag. Tandem cavity pairs residing within the combustor's constant area region exhibited a 16% improvement to combustion and a 10% increase in heat release compared to the equivalently fuelled single cavity. There was minimal difference in drag for these configurations at high fuelling. Negligible benefits emerged from any tandem configuration at moderate fuelling rates, and positioning a tandem cavity at the diverging portion universally provided no benefit.

著录项

获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号