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首页> 外文期刊>Acta astronautica >Numerical investigation of scramjet strut injector cooling for different fuel mass fluxes and strut material properties at mach 8 flight conditions
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Numerical investigation of scramjet strut injector cooling for different fuel mass fluxes and strut material properties at mach 8 flight conditions

机译：在8马赫飞行条件下不同燃料质量通量和支柱材料性能的冲压发动机支柱喷射器冷却的数值研究。

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摘要

The thermal load on a lobed scramjet (supersonic combustion ramjet) strut injector is investigated numerically for Mach 8 flight conditions. For this purpose, coupled 3D RANS (Reynolds Averaged Navier-Stokes) simulations of the supersonic external flow field around the strut injector and the subsonic strut internal hydrogen flow are performed. The temperature distribution in the solid strut material is simulated by a separate code, which exchanges data with the fluid solvers. Due to the predominantly low Mach numbers inside the strut, an all-Mach number preconditioning is required to enable convergence of the compressible flow solver. The air flow Mach number in the combustion chamber is three. Different strut materials (copper, silicone carbide, molybdenum, and tungsten) with different heat capacities and thermal conductivities are compared. Moreover, the impact of the height of the blunt tip of the strut on the heat load is investigated. Due to a small detached normal shock wave upstream of the strut, the temperatures at the tip become very high; this part is notably difficult to cool. In order to keep the strut temperatures acceptable, it is cooled actively by the hydrogen that is injected for combustion. A sophisticated internal strut structure is needed to direct the hydrogen towards regions of highest heat load. Different strut geometries, fuel mass fluxes (equivalence ratios), and strut materials are investigated.
机译：在8马赫飞行条件下，数值研究了带叶片超燃冲压发动机（超音速燃烧冲压喷气发动机）的喷射器上的热负荷。为此，对围绕支杆喷射器的超音速外部流场和亚音速支杆内部氢流进行了耦合3D RANS（雷诺平均Navier-Stokes）模拟。固体支撑材料中的温度分布由单独的代码模拟，该代码与流体求解器交换数据。由于支杆内部的马赫数主要较低，因此需要进行全马赫数预处理，以使可压缩流量求解器收敛。燃烧室内的空气马赫数为三。比较了具有不同热容量和热导率的不同支柱材料（铜，碳化硅，钼和钨）。此外，研究了撑杆钝头高度对热负荷的影响。由于支杆上游有一小段分离的法向冲击波，尖端的温度变得非常高。这部分很难冷却。为了使支柱温度保持在可接受的水平，它通过注入用于燃烧的氢气进行主动冷却。需要一种精密的内部支撑结构来将氢引导至热负荷最高的区域。研究了不同的支柱几何形状，燃料质量通量（当量比）和支柱材料。

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  • 来源
    《Acta astronautica》 |2019年第7期|353-364|共12页
  • 作者

    Gerlinger Peter; Simsont Yann Hendrik;

  • 作者单位

    Univ Stuttgart, Inst Combust Technol Aerosp Engn, Pfaffenwaldring 38-40, D-70569 Stuttgart, Germany;

    Univ Stuttgart, Inst Combust Technol Aerosp Engn, Pfaffenwaldring 38-40, D-70569 Stuttgart, Germany;

  • 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

    Scramjet; Strut injector; Conjugate heat transfer; Strut cooling;

    机译：Scramjet;支撑杆喷射器;共轭传热;支撑杆冷却;

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