宇航学报

宇航学报 ›› 2017, Vol. 38 ›› Issue (1): 80-88.doi: 10.3873/j.issn.1000-1328.2017.01.011

• 推进技术与动力 • 上一篇    下一篇

高马赫数来流超燃冲压发动机燃烧流场分析

张时空，李江，黄志伟，秦飞，薛瑞   

  1. 西北工业大学燃烧、热结构和内流场重点试验室，西安710072
  • 收稿日期:2016-04-15 修回日期:2016-11-07 出版日期:2017-01-15 发布日期:2017-01-25
  • 基金资助:

    国家自然科学基金（91541110）

Combustion Flow Field Analysis of a Scramjet Engine at High Mach Number

ZHANG Shi kong, LI Jiang, HUANG Zhi wei, QIN Fei, XUE Rui   

  1. Science and Technology on Combustion, Internal Flow and Thermo structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China
  • Received:2016-04-15 Revised:2016-11-07 Online:2017-01-15 Published:2017-01-25

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摘要：

以模拟自由来流马赫数12的地面试验氢燃料超燃冲压发动机为研究对象，应用商用计算流体力学软件CFD++；针对高马赫数来流下的超燃冲压发动机的典型流场结构、空间释热分布、预混/非预混燃烧模式和火焰稳定机理开展了分析研究。计算中采用7组分、9反应步的氢气/氧气动力学模型，使用壁面函数结合两方程剪应力输运模型，基于雷诺时均化方法开展计算，数值结果与试验数据相符较好。1）验证了CFD++软件在高马赫数来流下的适用性和计算精度；2）分析了高超声速来流下的燃烧室流场特征；3）获得了高马赫来流条件下的发动机燃烧效率、释热区间、预混/非预混燃烧模式的空间分布规律；4）为进一步开展高马赫数下的发动机精细化流场计算和多尺度燃烧过程研究提供了重要依据。

关键词: 超燃冲压发动机, 高马赫数；燃烧模式；数值模拟

Abstract:

A hydrogen-fueled ground testing scramjet engine operating at flight Ma 12 is numerically studied. Computation of the combustion field is carried out based on the commercial software CFD++. The basic flow structure, the spatial distribution of heat release, the combustion mode of premixed/non-premixed, and the mechanism of flame stabilization of the scramjet engine which works at Ma 12 are investigated in detail. A hydrogen-air chemistry kinetic model consisting of 7 species, 9 reaction steps is adopted in the Reynolds-Averaged Navier-Stokes simulation. The two-equation shear-stress-transport(SST) turbulence model which takes account of the wall functions is used to handle the turbulence-chemistry interactions. The results are validated by the experimentally measured wall pressure distribution with good agreement. 1） The applicability and accuracy of CFD++ in the study of compressible reactive flows under high flight Mach numbers are verified; 2）the combustion characteristics under hypersonic inflow conditions are studied; 3) the combustion efficiency, the heat release, and the combustion mode are obtained for the very high Mach number; 4）these observations offer insight into the potential for exploring the mechanisms of the combustion simulation and multi-scale combustion dynamics under hypersonic flow conditions.

Key words: Scramjet, High Mach number, Combustion mode, Numerical simulation

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