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首页> 外文期刊>Journal of turbomachinery >Fan Root Aerodynamics for Large Bypass Gas Turbine Engines: Influence on the Engine Performance and 3D Design
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Fan Root Aerodynamics for Large Bypass Gas Turbine Engines: Influence on the Engine Performance and 3D Design

机译：大型旁路燃气涡轮发动机的风扇根空气动力学：对发动机性能和3D设计的影响

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摘要

The exit flow field of the fan root of large turbofan engines defines the inlet conditions to the core compressor. This in turn could have significant impact to the performance of the core compressor. This study is aimed to resolve two related issues concerning the impact of the fan root flow on the core compressor performance: to establish the effect of an increased loss at the inlet on the engine specific fuel consumption (SFC) and to assess the effect of the radial distribution of the fan root flow on the engine performance. With understanding of these issues, the geometric parameters and design details which can produce a more uniform core flow at the exit of the fan stage module can be identified. The fan root flow is analyzed with methods of different complexity and fidelity. A simple cycle analysis is used to assess the impact on engine SFC of a stagnation pressure deficit at the fan root; a throughflow code is used for the preliminary study of the curvature effect of the root flow path, and 3D RANS CFD calculations are then used to simulate the flow path from the inlet of the fan to the first stage of the core compressor. The adequacy of the application of the numerical code in this case has been assessed and confirmed by the comparison with the experimental data for two rig configurations. The results of this study show that the flow at the fan hub region is very complex and dominated by 3D effects. The interaction of the secondary flow with real geometries, such as leakage flows, is found to have a strong detrimental effect on the core performance. The curvature of the hub end wall is a key parameter controlling the fan root flow topology; it influences the strength of the secondary flow, the spanwise distribution of the flow, and its sensitivity to leakage flow. With this understanding, it is possible to redesign of the fan hub flow path to reduce the loss generation by a significant amount.
机译：大型涡轮风扇发动机的风扇根部的出口流场决定了核心压缩机的进气条件。反过来，这可能会对核心压缩机的性能产生重大影响。这项研究旨在解决与风机根流对核心压缩机性能的影响有关的两个相关问题：确定进气口损失增加对发动机比油耗（SFC）的影响，并评估进气口的损失。风扇根流的径向分布对发动机性能的影响。了解了这些问题后，就可以确定可以在风扇级模块出口处产生更均匀的核心流的几何参数和设计细节。用不同复杂度和保真度的方法分析风扇根流。简单的循环分析可用来评估风扇根部停滞压力不足对发动机SFC的影响。使用通流代码初步研究根部流动路径的曲率效应，然后使用3D RANS CFD计算来模拟从风扇入口到核心压缩机第一级的流动路径。通过与两种钻机配置的实验数据进行比较，已经评估并证实了在这种情况下应用数字代码的适当性。这项研究的结果表明，风扇轮毂区域的流动非常复杂，并且受3D效果支配。发现次级流与实际几何形状（例如泄漏流）的相互作用对岩心性能有很大的不利影响。轮毂端壁的曲率是控制风扇根部流动拓扑的关键参数。它会影响次级流的强度，流的跨度分布及其对泄漏流的敏感性。有了这种理解，就可以重新设计风扇毂的流路，以大大减少损耗的产生。

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  • 来源
    《Journal of turbomachinery》 |2012年第6期|p.061017.1-061017.11|共11页
  • 作者

    Giulio Zamboni; Liping Xu;

  • 作者单位

    Whittle Laboratory, Department of Engineering, University of Cambridge, Cambridge, CB3 0DY, UK;

    Whittle Laboratory, Department of Engineering, University of Cambridge, Cambridge, CB3 0DY, UK;

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