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首页> 外文期刊>Fuel >Experimental study on combustion modes of a liquid kerosene fueled RBCC combustor
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Experimental study on combustion modes of a liquid kerosene fueled RBCC combustor

机译：液体煤油燃料的RBCC燃烧器燃烧模式的实验研究

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摘要

To enable the dual-mode scramjet engine operate in the whole flight trajectory, the urgent development of the Rocket Based Combined Cycle (RBCC) propulsion system has been put forward. The behavior of ram-scram combustion mode transition was examined using direct-connect experiments of a model RBCC combustor along with pressure measurements. At an inflow stagnation condition of P-0 = 1.5 MPa and T-0 = 1280 K, four combustion modes, namely weak combustion mode, rocket-scram mode, rocketram mode and ram mode were classified through wall pressure distributions, combustor inlet Mach number, and flame plume visualization. Both the position of fuel strut injectors and the cavity installation location had a significant effect on RBCC combustion modes. When rocket jets were added, the change of the fuel strut position could cause mode transition. Furthermore, as the rockets were turned off, different locations where the cavities were installed could lead mode transition as well. When the primary heat release zone was stabilized at the downstream in the combustor, the addition of rocket jets would make the burning zone jump to upstream abruptly. The discovery of this phenomenon provided a new method and feasible strategy for mode transition. (C) 2017 Elsevier Ltd. All rights reserved.
机译：为了使双模超燃冲压发动机能够在整个飞行轨迹上运行，已经提出了基于火箭的联合循环（RBCC）推进系统的紧迫发展。使用模型RBCC燃烧器的直接连接实验以及压力测量来检查ram-scram燃烧模式过渡的行为。在P-0 = 1.5 MPa和T-0 = 1280 K的进气停滞条件下，通过壁压力分布，燃烧室进气口马赫数将四种燃烧模式，即弱燃烧模式，火箭-超燃模式，火箭-超燃模式和冲压-模式分类。和火焰羽可视化。燃料支撑喷油嘴的位置和腔体的安装位置对RBCC燃烧模式都有重要影响。添加火箭喷射器后，燃油支撑杆位置的改变可能会导致模式转换。此外，由于关闭了火箭，安装空腔的不同位置也可能导致模式转换。当一次放热区稳定在燃烧室的下游时，增加火箭射流会使燃烧区突然跳到上游。这一现象的发现为模式转换提供了新的方法和可行的策略。 （C）2017 Elsevier Ltd.保留所有权利。

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  • 来源
    《Fuel》 |2017年第1期|433-444|共12页
  • 作者

    Xue Rui; He Guoqiang; Wei Xianggeng; Hu Chunbo; Tang Xiang; Weng Chao;

  • 作者单位

    Xi An Jiao Tong Univ, Sch Aerosp, Xian 710049, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Peoples R China;

    Tongji Univ, Shanghai 200092, Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Rocket Based Combined Cycle Combustor; Combustion mode; Ram-scram mode transition;

    机译：基于火箭的联合循环燃烧器;燃烧模式;Ram-Scram模式转换;

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