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首页> 外文期刊>Fuel >On burnout performance of a rocket-engine-based incinerator devised for high burning rate of solid particles
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On burnout performance of a rocket-engine-based incinerator devised for high burning rate of solid particles

机译：基于火箭发动机的焚化炉的燃尽性能研究，该焚化炉专为高固体颗粒燃烧率而设计

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摘要

A rocket-engine-based incinerator is proposed as a compact device of a solid-particle incinerator for high-performance burnout of wastes with solid phase. Burnout performance is investigated numerically in the chamber devised for this purpose. The present chamber employs design concepts of swirl flow and nozzle shape applied to a furnace of power-plants and a rocket combustor, respectively. As the first step, non-reactive flow field is analyzed in the incinerator with primary injectors and secondary injectors through which coal fuel and air are supplied. Deflection angle of a primary injector, incline angle of a secondary injector, gap between two-type injectors are selected as design parameters. Swirl number is adopted for evaluation of the degree of swirl flow and it is estimated over wide ranges of three parameters. Swirl number varies non-monotonically depending on the combination of the parameters. Burnout ratio increases with swirl number. High swirl number is attained over broad ranges of deflection and incline angles. From the numerical results, the design points with high burning performance can be found by maximizing swirl number. The proposed chamber has been verified to attain higher burnout performance than a conventional incinerator by a factor of 10.
机译：提出了一种基于火箭发动机的焚化炉，作为固体颗粒焚化炉的紧凑装置，用于高效燃烧含固相废物。在为此目的而设计的燃烧室中，对燃尽性能进行了数值研究。本腔室采用了分别应用于发电厂的炉子和火箭燃烧器的旋流和喷嘴形状的设计概念。第一步，在具有主喷射器和副喷射器的焚化炉中分析非反应流场，通过主喷射器和次喷射器供应煤燃料和空气。选择主喷射器的偏转角，副喷射器的倾斜角，两种类型的喷射器之间的间隙作为设计参数。旋流数用于评估旋流的程度，并在三个参数的较大范围内进行估算。旋流数根据参数的组合非单调变化。燃尽率随着旋流数的增加而增加。在较大的偏转角和倾斜角范围内都可获得高涡旋数。从数值结果可以看出，通过最大化旋流数可以找到具有高燃烧性能的设计点。经过验证，拟议的燃烧室具有比传统焚化炉更高的燃尽性能，提高了10倍。

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  • 来源
    《Fuel》 |2014年第ptaa期|478-487|共10页
  • 作者

    Jin Woo Son; Su Ho Kim; Chae Hoon Sohn;

  • 作者单位

    Department of Mechanical Engineering, Sejong University, Seoul 143-747, Republic of Korea;

    Department of Mechanical Engineering, Sejong University, Seoul 143-747, Republic of Korea;

    Department of Mechanical Engineering, Sejong University, Seoul 143-747, Republic of Korea;

  • 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-engine-based incinerator; Nozzle; Swirl number; Solid particle; Burnout ratio;

    机译：基于火箭发动机的焚化炉;喷嘴;旋流号;固体颗粒;倦怠率;

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