Aerothermal predictions of combustor/turbine interactions using advanced turbulence modeling

13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics Pub Date : 1900-01-01 DOI:10.29008/ETC2019-050

F. Cottier, Pierre Pinchaud, G. Dumas

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引用次数: 2

Abstract

The flow and temperature fields out of a combustion chamber are characterized by high variations, spatially and temporarily. This also results in high turbulence generation. The downstream turbine stage is subject to swirling hot spots and therefore to gradients that have to be taken into account in the design and sizing of the turbine components. In addition, these spots are transported further downstream through the turbine and interact with secondary turbine flows. This paper presents comparisons between numerical calculations and measurements carried out in a cold combustor simulator – a turbine rig representative for engine OTDF and RTDF. The traverse measurements recorded after each airfoil row are compared with CFD calculations of a full turbine model including ID disc cavities. Simulating simultaneously the cold combustor and the turbine allows taking these temporal variations into account. The configuration has been computed using conventional RANS-URANS methods as well as Scale-Adaptative Simulation (SAS) for turbulence modeling, and shows that this advanced model improved the hot/cold mixing significantly.

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使用先进湍流模型的燃烧室/涡轮相互作用的气动热预测

燃烧室外的流场和温度场具有很大的时空变化特征。这也导致了高湍流的产生。下游涡轮级受到旋转热点的影响，因此在涡轮部件的设计和尺寸中必须考虑到梯度。此外，这些斑点通过涡轮进一步向下游输送，并与二次涡轮流动相互作用。本文介绍了在冷燃烧室模拟器中进行的数值计算和测量的比较，该模拟器是发动机OTDF和RTDF的代表涡轮钻机。每个翼型排后记录的横掠测量值与包含内径盘腔的全涡轮模型的CFD计算结果进行了比较。同时模拟冷燃烧室和涡轮机允许考虑这些时间变化。利用传统的ranss - urans方法和尺度自适应模拟(SAS)进行了紊流模拟计算，结果表明，这种先进的模型显著改善了热/冷混合。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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