...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Advanced Combustor Concepts for Low Emissions Supersonic Propulsion
【24h】

Advanced Combustor Concepts for Low Emissions Supersonic Propulsion

机译：低排放超音速推进的先进燃烧器概念

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

摘要

Novel lean-burn combustor concepts were designed and evaluated for supersonic aircraft propulsion, with a focus on cruise NO_x emissions. Premixing to lean conditions is especially challenging at supersonic cruise because combustor inlet temperatures are high and autoignition times are short. However, combustor pressure is significantly lower than at takeoff, so at cruise this allows heated jet fuel to be vaporized before injection as an aid to mixing. Two concepts-differentiated by swirler aerodynamics, swirler size, and staging method-were evaluated in the work reported here, both using injection of vaporized jet fuel. Computational fluid dynamics (CFD) calculations of mixing and combustion were used to design hardware for each concept. Injectors for each were fabricated using stereolithography (SLA) for cold-flow mixing tests, and using metal fabrication for subsequent combustion tests. Combustion test results show that emissions index for NO_x (EINO_x) ＜ 5 was achieved for both concepts in single-sector tests at supersonic cruise combustor conditions.
机译：针对超音速飞机推进器设计并评估了新型稀薄燃烧器概念，并着重于巡航NO_x排放。在超音速巡航中，将混合气预混合到稀薄的条件下尤其具有挑战性，因为燃烧室的入口温度高，自燃时间短。但是，燃烧室压力明显低于起飞时的压力，因此在巡航时，这可以使加热的喷气燃料在喷射之前蒸发，从而有助于混合。在本文报道的工作中，评估了通过旋流器空气动力学特性，旋流器尺寸和分级方法区分的两个概念，均使用喷射的喷气燃料。混合和燃烧的计算流体力学（CFD）计算用于为每个概念设计硬件。使用立体光刻（SLA）制造用于冷流混合测试的每种喷射器，并使用金属制造进行后续燃烧测试。燃烧测试结果表明，在超音速巡航燃烧器条件下的单扇区测试中，这两个概念均实现了NO_x（EINO_x）＜5的排放指数。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
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