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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Numerical Study of Aerodynamic Losses of Effusion Cooling Holes in Aero-Engine Combustor Liners
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Numerical Study of Aerodynamic Losses of Effusion Cooling Holes in Aero-Engine Combustor Liners

机译：航空发动机燃烧室衬里喷孔冷却空气损失的数值研究

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Due to the stringent cooling requirements of novel aero-engines combustor liners, a comprehensive understanding of the phenomena concerning the interaction of hot gases with typical coolant jets plays a major role in the design of efficient cooling systems. In this work, an aerodynamic analysis of the effusion cooling system of an aero-engine combustor liner was performed; the aim was the definition of a correlation for the discharge coefficient (C_D) of the single effusion hole. The data were taken from a set of CFD RANS (Reynolds-averaged Navier-Stokes) simulations, in which the behavior of the effusion cooling system was investigated over a wide range of thermo/fluid-dynamics conditions. In some of these tests, the influence on the effusion flow of an additional air bleeding port was taken into account, making it possible to analyze its effects on effusion holes C_D. An in depth analysis of the numerical data set has pointed out the opportunity of an efficient reduction through the ratio of the annulus and the hole Reynolds numbers: The dependence of the discharge coefficients from this parameter is roughly linear. The correlation was included in an in-house one-dimensional thermo/fluid network solver, and its results were compared with CFD data. An overall good agreement of pressure and mass flow rate distributions was observed. The main source of inaccuracy was observed in the case of relevant air bleed mass flow rates due to the inherent three-dimensional behavior of the flow close to bleed opening. An additional comparison with experimental data was performed in order to improve the confidence in the accuracy of the correlation: Within the validity range of pressure ratios in which the correlation is defined (>1.02), this comparison pointed out a good reliability in the prediction of discharge coefficients. An approach to model air bleeding was then proposed, with the assessment of its impact on liner wall temperature prediction.
机译：由于新型航空发动机燃烧室衬套对冷却的严格要求，对有关热气体与典型冷却液喷嘴相互作用的现象的全面理解在有效冷却系统的设计中起着重要作用。在这项工作中，对航空发动机燃烧室衬套的排放冷却系统进行了空气动力学分析。目的是定义单个积水孔的排放系数（C_D）的相关性。数据来自一组CFD RANS（雷诺平均Navier-Stokes）模拟，其中在广泛的热/流体动力学条件下研究了渗出冷却系统的行为。在这些测试中的某些测试中，考虑了对其他排气孔的流出流量的影响，从而有可能分析其对流出孔C_D的影响。数值数据集的深入分析指出了通过环空比和孔雷诺数的比率有效减小的机会：放电系数与该参数的相关性大致为线性。相关关系包含在内部一维热/流体网络求解器中，并将其结果与CFD数据进行比较。观察到压力和质量流量分布的总体良好一致性。在相关的排气质量流率的情况下，观察到不准确的主要原因，这是由于靠近排气口的气流固有的三维行为。为了提高对相关性准确性的置信度，还与实验数据进行了比较：在定义相关性的压力比的有效范围内（> 1.02），该比较指出了预测压力相关性的良好可靠性。放电系数。然后提出了一种模拟空气渗漏的方法，并评估了其对衬砌壁温度预测的影响。

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