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Application and theoretical analysis of the flamelet model for supersonic turbulent combustion flows in the scramjet engine

机译：火焰喷射模型在超燃冲压发动机超音速湍流燃烧中的应用及理论分析

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摘要

In the framework of Reynolds-averaged Navier-Stokes simulation, supersonic turbulent combustion flows at the German Aerospace Centre (DLR) combustor and Japan Aerospace Exploration Agency (JAXA) integrated scramjet engine are numerically simulated using the flamelet model. Based on the DLR combustor case, theoretical analysis and numerical experiments conclude that: the finite rate model only implicitly considers the large-scale turbulent effect and, due to the lack of the small-scale non-equilibrium effect, it would overshoot the peak temperature compared to the flamelet model in general. Furthermore, high-Mach-number compressibility affects the flamelet model mainly through two ways: the spatial pressure variation and the static enthalpy variation due to the kinetic energy. In the flamelet library, the mass fractions of the intermediate species, e.g. OH, are more sensible to the above two effects than the main species such as H2O. Additionally, in the combustion flowfield where the pressure is larger than the value adopted in the generation of the flamelet library or the conversion from the static enthalpy to the kinetic energy occurs, the temperature obtained by the flamelet model without taking compressibility effects into account would be undershot, and vice versa. The static enthalpy variation effect has only little influence on the temperature simulation of the flamelet model, while the effect of the spatial pressure variation may cause relatively large errors. From the JAXA case, it is found that the flamelet model cannot in general be used for an integrated scramjet engine. The existence of the inlet together with the transverse injection scheme could cause large spatial variations of pressure, so the pressure value adopted for the generation of a flamelet library should be fine-tuned according to a pre-simulation of pure mixing.
机译：在雷诺平均Navier-Stokes模拟的框架内，使用小火焰模型对德国航空航天中心（DLR）燃烧室和日本航空航天局（JAXA）集成超燃冲压发动机的超音速湍流燃烧流进行了数值模拟。基于DLR燃烧室的情况，理论分析和数值实验得出的结论是：有限速率模型仅隐含考虑了大尺度的湍流效应，由于缺乏小尺度的非平衡效应，它将使峰值温度超调。与一般的小火焰模型相比。此外，高马赫数可压缩性主要通过两种方式影响小火焰模型：动能引起的空间压力变化和静态焓变。在小火焰库中，中间物种的质量分数，例如OH对上述两种作用比H2O等主要物质更敏感。另外，在燃烧流场中，压力大于在生成小火焰库中采用的值或发生从静态焓到动能的转换时，通过小火焰模型获得的温度将不考虑可压缩性的影响。打底，反之亦然。静态焓变效应对火焰模型的温度模拟影响很小，而空间压力变化的效应可能会引起较大的误差。从JAXA案例中可以发现，小火焰模型通常不能用于集成超燃冲压发动机。进气口的存在以及横向注入方案可能导致压力的较大空间变化，因此应根据纯混合的预模拟对用于生成小火焰库的压力值进行微调。

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