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首页> 外文期刊>The Aeronautical Journal >Reacting flow analysis of a cavity-based scramjet combustor using a Jacobian-free Newton-Krylov method
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Reacting flow analysis of a cavity-based scramjet combustor using a Jacobian-free Newton-Krylov method

机译：基于无雅可比牛顿-克雷洛夫方法的基于腔的超燃冲压燃烧室的反应流分析

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The scramjet is a rather a new technology and there are many issues related to their operation, especially when it comes to the combustion processes. Combustion in high-speed flows causes various problems such as flame instability and poor fuel-air mixing efficiency. One of the methods used to overcome these problems is to recess a cavity in the combustor wall where a secondary flow is generated. In this study, a computational fluid dynamics (CFD) code is developed to analyse the reacting flow passing through the cavity-based scramjet combustor. The developed code is based on three-dimensional coupled Navier-Stokes and finite rate chemistry equations. An ethylene-air reduced chemical reaction model is used as a fuel-air combination. The Spalart-Allmaras model is utilised for turbulence closure. The non-dimensional form of the flow and chemical reaction equations are discretised using a finite volume method. The Jacobian-Free Newton-Krylov (JFNK) method is used to solve the coupled system of non-linear equations. The JFNK is a matrix-free solution method which improves the computational cost of Newton's method. The parameters that affect the performance of the JFNK method are studied in the analysis of a scramjet combustor. The influence of the forcing term on the convergence of the JFNK method is studied in the analysis of scramjet combustor. Different upwind flux vector splitting methods are utilised. Various flux limiter techniques are employed for the calculations of higher order flux vectors. The effects of flux vector splitting and flux limiter methods on the convergence and accuracy of the JFNK method are evaluated. Moreover, the variations of the mixing efficiency with fuel injection angles are studied.
机译：超燃冲压发动机是一项相当新的技术，与它们的运行有关的问题很多，尤其是在燃烧过程中。高速流动中的燃烧引起各种问题，例如火焰不稳定和不良的燃料-空气混合效率。用于克服这些问题的方法之一是在燃烧器壁上凹入空腔，在该空腔中产生二次流。在这项研究中，计算流体动力学（CFD）代码被开发来分析通过基于腔的超燃冲压燃烧器的反应流。开发的代码基于三维耦合的Navier-Stokes和有限速率化学方程式。乙烯-空气还原的化学反应模型用作燃料-空气组合。 Spalart-Allmaras模型用于湍流封闭。流量和化学反应方程的无量纲形式使用有限体积法离散化。使用无雅可比牛顿-克里洛夫（JFNK）方法求解非线性方程组的耦合系统。 JFNK是一种无矩阵求解方法，可提高牛顿法的计算成本。在超燃冲压燃烧器的分析中研究了影响JFNK方法性能的参数。在超燃冲压燃烧器的分析中研究了强迫项对JFNK方法收敛性的影响。使用了不同的迎风通量矢量分裂方法。各种通量限制器技术用于计算高阶通量向量。评估了磁通矢量分裂和磁通限制器方法对JFNK方法的收敛性和准确性的影响。此外，研究了混合效率随燃料喷射角的变化。

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