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首页> 外文会议>ASME Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >DESIGN AND ANALYSIS OF A HIGH STAGE LOADING FIVE-STAGE LP TURBINE RIG EMPLOYING IMPROVED TRANSITION MODELING
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DESIGN AND ANALYSIS OF A HIGH STAGE LOADING FIVE-STAGE LP TURBINE RIG EMPLOYING IMPROVED TRANSITION MODELING

机译：改进过渡模型的高负荷五级低压汽轮机钻机的设计与分析

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摘要

Modern aircraft engine designs have to realize high performance while managing important weight and cost issues. For high bypass ratio engines this results in high demands for the low pressure turbine component. The combination of a low speed parameter due to large fan diameters with reduced number of turbine stages due to weight and cost considerations leads to high stage loading requirements. Realizing high turbine efficiencies at low Reynolds Number operation at high altitudes for these high stage loadings is a key for state-of-the-art turbofan engines. For the aerodynamic design, high stage loading factors directly translate into increased airfoil flow turning. These increased turning levels have to be realized in combination with elevated airfoil load in order to keep low airfoil counts. This is particularly challenging in combination and requires minimization of negative effects on the airfoil losses and secondary losses. In this paper the development of a five-stage turbine with high stage loading is discussed with focus on the aerodynamic design. A specially designed cascade test has been part of the turbine design, which showed the need for improvement of the transition modeling within the CFD code used for design and analysis. The derived modeling enhancement is then employed for the analysis of the five-stage rig, which was tested at the altitude test facility at Stuttgart University. The modeling achieved significant improvements in the quality of the numerical results. The analysis includes sensitivities to Reynolds number and a detailed view of the suction side flow.
机译：现代飞机发动机设计必须在管理重要的重量和成本问题的同时实现高性能。对于高旁通比发动机，这导致对低压涡轮部件的高要求。由于风扇直径大而导致的低速参数与由于重量和成本的考虑而导致的涡轮级数减少的结合，导致了对级负载的高要求。对于这些高水平载荷，在高海拔下以低雷诺数运行时实现高涡轮效率是最先进的涡扇发动机的关键。对于空气动力学设计，高阶载荷因子直接转化为增加的翼型流转向。这些增加的转弯水平必须结合增加的翼型载荷来实现，以保持低的翼型数量。这在组合中特别具有挑战性，并且需要最小化对翼型损失和二次损失的负面影响。在本文中，以空气动力学设计为重点，讨论了具有高负荷的五级涡轮机的开发。涡轮机设计的一部分已经特别设计了级联测试，该测试表明需要在用于设计和分析的CFD代码中改进过渡建模。然后，将派生的建模增强功能用于五阶段钻机的分析，该钻机已在斯图加特大学的海拔测试设施进行了测试。该建模在数值结果的质量上取得了重大改进。该分析包括对雷诺数的敏感性和吸入侧流的详细视图。

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