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Reduction of surface friction drag in scramjet engine by boundary layer combustion

机译：边界层燃烧减少瘙痒动发动机的表面摩擦拖曳

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摘要

This study investigates the effects of boundary layer combustion on skin friction reduction in a model scramjet combustor. The 4-equation RANS model (Transition SST model) is employed as the turbulence model and one experimental case which involves supersonic turbulent boundary layer combustion is used for validating the numerical simulation method. Then a wall jet device which can be used to inject hydrogen into boundary layer is designed and added to the lower wall of the combustor in the model scramjet engine. The numerical results showed that the optimal ratio between the primary fuel, producing thrust, and the wall jet fuel, used for drag reduction, for getting the largest skin-friction drag reduction when installing the wall jet device in the combustor, is 3:1. The study of modifying the location of the wall jet device showed that setting the wall jet position too close to the upstream or downstream could not get the maximum overall drag reduction. The installation position in the flow path depends on the coupling of primary fuel and wall jet fuel combustion. In practical scramjet design, the distribution ratio of primary to wall jet fuel and the location of wall jet device should be weighed to improve skin friction reduction efficiency and overall engine performance. (C) 2021 Elsevier Masson SAS. All rights reserved.
机译：本研究调查了边界层燃烧对模型扰燃机燃烧室皮肤摩擦减少的影响。 4 - 等式RAN模型（转换SST模型）用作湍流模型，并且涉及超声波湍流边界层燃烧的一个实验情况用于验证数值模拟方法。然后，可以用于将氢气喷射到边界层中的壁射流装置被设计并在模型Scramjet发动机中添加到燃烧器的下壁上。数值结果表明，用于减压的主要燃料，生产推力和壁射燃料之间的最佳比率，用于在燃烧器中安装壁式喷射装置时获得最大的肌肤摩擦减阻，是3：1 。改变墙面喷射装置的位置的研究表明，将壁式喷射位置设置得太靠近上游或下游无法获得最大的整体减阻。流路中的安装位置取决于初级燃料和壁射流燃烧的耦合。在实用的斯普拉克喷射设计中，应称重初级到壁式喷射燃料的分配比和壁式喷射装置的位置，以提高皮肤摩擦降低效率和整体发动机性能。 （c）2021 Elsevier Masson SAS。版权所有。

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  • 来源
    《Aerospace science and technology》 |2021年第8期|106788.1-106788.16|共16页
  • 作者

    Xue Rui; Zheng Xing; Yue Lianjie; Zhang Qian; He Xin; Yang Jing; Weng Chao; Li Zhihao;

  • 作者单位

    Xi An Jiao Tong Univ Sch Aerosp State Key Lab Strength & Vibrat Mech Struct Shaanxi Engn Lab Vibrat Control Aerosp Struct Xian 710049 Peoples R China|Chinese Acad Sci Inst Mech State Key Lab High Temp Gas Dynam Beijing 100190 Peoples R China|YuelaiYH Co Guiyang 550000 Peoples R China;

    Xi An Jiao Tong Univ Sch Aerosp State Key Lab Strength & Vibrat Mech Struct Shaanxi Engn Lab Vibrat Control Aerosp Struct Xian 710049 Peoples R China;

    Chinese Acad Sci Inst Mech State Key Lab High Temp Gas Dynam Beijing 100190 Peoples R China;

    Xi An Jiao Tong Univ Sch Aerosp State Key Lab Strength & Vibrat Mech Struct Shaanxi Engn Lab Vibrat Control Aerosp Struct Xian 710049 Peoples R China;

    Xi An Jiao Tong Univ Sch Aerosp State Key Lab Strength & Vibrat Mech Struct Shaanxi Engn Lab Vibrat Control Aerosp Struct Xian 710049 Peoples R China;

    Xi An Jiao Tong Univ Sch Aerosp State Key Lab Strength & Vibrat Mech Struct Shaanxi Engn Lab Vibrat Control Aerosp Struct Xian 710049 Peoples R China|YuelaiYH Co Guiyang 550000 Peoples R China;

    YuelaiYH Co Guiyang 550000 Peoples R China|Tongji Univ Shanghai 200092 Peoples R China;

    Xian Modern Control Technol Res Inst Xian 710065 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

    Boundary layer combustion; Skin-friction reduction; Supersonic combustion; Scramjet engine;

    机译：边界层燃烧;减少皮肤摩擦;超音速燃烧;Scramjet引擎;

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