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Aerodynamic Instabilities of Swept Airfoil Design in Transonic Axial-Flow Compressors

机译：跨音速轴流压气机后掠翼型设计的空气动力学不稳定性

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摘要

This paper investigates the effect of a swept airfoil design on the aerodynamic instabilities of transonic axial-flow compressors based on global stability analysis. An approach aimed at predicting the stall inception point is developed by integrating an improved blade force model and a new mathematical treatment method for steady flow. This approach takes both the concrete blade geometry and complicated base flow into consideration, which promises to provide a highly efficient assessment of the stall margin of a compressor in the design phase. Specifically, the relevant validation is conducted through a typical transonic axial-flow compressor, which shows that the predicted stall inception point agrees well with the experimental result. Furthermore, the compressor is also adopted as a prototype, from which a series of forward- and backward-swept rotors are modeled. Aerodynamic instabilities in the form of eigenvalues for each swept rotor, along with the throttling process, are predicted by solving the developed stall inception model. The comparison of the predicted results for these rotors shows that the backward sweep deteriorates the stall margin; the larger the backward-swept degree, the poorer the compressor stability becomes. However, the forward sweep does not exhibit remarkable and regular influence on the stall margin of the compressor in the present research. A discussion of the predicted results is made from the perspectives of blade loading and passage shock location.
机译：本文基于整体稳定性分析，研究了后掠翼型设计对跨音速轴流压缩机空气动力学不稳定性的影响。通过整合改进的叶片力模型和新的稳流数学处理方法，开发了一种用于预测失速开始点的方法。这种方法同时考虑了混凝土叶片的几何形状和复杂的基流，这有望在设计阶段对压缩机的失速裕度进行高效评估。具体而言，通过典型的跨音速轴流式压缩机进行相关验证，这表明预测的失速开始点与实验结果非常吻合。此外，该压缩机也被用作原型，从中建模了一系列的前掠和后掠转子。通过求解已开发的失速开​​始模型，可以预测每个扫掠转子的特征值形式的空气动力学不稳定性以及节流过程。对这些转子的预测结果的比较表明，向后扫掠会恶化失速裕度；反之，后掠度越大，压缩机的稳定性越差。然而，在本研究中，前掠并未对压缩机的失速裕度表现出明显的规律性影响。从叶片载荷和通道冲击位置的角度对预测结果进行了讨论。

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  • 来源
    《AIAA Journal》 |2018年第5期|1878-1893|共16页
  • 作者

    He Chen; Ma Yunfei; Liu Xiaohua; Sun Dakun; Sun Xiaofeng;

  • 作者单位

    Beihang Univ, Sch Energy & Power Engn, Beijing 100191, Peoples R China;

    Beihang Univ, Sch Energy & Power Engn, Beijing 100191, Peoples R China;

    Shanghai Jiao Tong Univ, Sch Aeronaut & Astronaut, Shanghai 200240, Peoples R China;

    Beihang Univ, Sch Energy & Power Engn, Coinnovat Ctr Adv Aeroengine, Beijing 100191, Peoples R China;

    Beihang Univ, Sch Energy & Power Engn, Coinnovat Ctr Adv Aeroengine, Beijing 100191, Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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