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首页> 外文期刊>Combustion Science and Technology >Numerical Prediction of the Flame Describing Function and Thermoacoustic Limit Cycle for a Pressurized Gas Turbine Combustor
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Numerical Prediction of the Flame Describing Function and Thermoacoustic Limit Cycle for a Pressurized Gas Turbine Combustor

机译：加压燃气轮机燃烧器的火焰描述函数和热声极限循环的数值预测

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摘要

The forced flame responses in a pressurized gas turbine combustor are predicted using numerical reacting flow simulations. Two incompressible(1) large eddy simulation solvers are used, applying two combustion models and two reaction schemes (4-step and 15-step) at two operating pressures (3 and 6 bar). Although the combustor flow field is little affected by these factors, the flame length and heat release rate are found to depend on combustion model, reaction scheme, and combustor pressure. The flame responses to an upstream velocity perturbation are used to construct the flame describing functions (FDFs). The FDFs exhibit smaller dependence on the combustion model and reaction chemistry than the flame shape and mean heat release rate. The FDFs are validated by predicting combustor thermoacoustic stability at 3 and 6 bar and, for the unstable 6 bar case, also by predicting the frequency and oscillation amplitude of the resulting limit cycle oscillation. All of these numerical predictions are in very good agreement with experimental measurements.
机译：使用数值反应流模拟预测了加压燃气轮机燃烧室中的强制火焰响应。使用两个不可压缩的（1）大涡模拟求解器，在两个工作压力（3和6 bar）下应用两个燃烧模型和两个反应方案（4步和15步）。尽管燃烧器的流场几乎不受这些因素的影响，但火焰长度和放热率却取决于燃烧模型，反应方案和燃烧器压力。火焰对上游速度扰动的响应用于构造火焰描述函数（FDF）。与火焰形状和平均放热率相比，FDF对燃烧模型和反应化学的依赖性更小。通过预测燃烧器在3 bar和6 bar的热声稳定性来验证FDF，对于不稳定的6 bar情况，还可以通过预测极限循环振荡的频率和振幅来验证FDF。所有这些数值预测都与实验测量非常吻合。

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