Analysis of three-dimensional blading influence on highly loaded transonic fan stator

XU Peng-fei; LIU Bao-jie; ZHAO Bin

Chinese

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Analysis of three-dimensional blading influence on highly loaded transonic fan stator

更新时间：2026-07-07

- Analysis of three-dimensional blading influence on highly loaded transonic fan stator
- Vol. 27, Issue 3, (2012)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院航空发动机气动热力国防科技重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
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XU Peng-fei, LIU Bao-jie, ZHAO Bin. Analysis of three-dimensional blading influence on highly loaded transonic fan stator[J]. 2012, 27(3).
DOI：

XU Peng-fei, LIU Bao-jie, ZHAO Bin. Analysis of three-dimensional blading influence on highly loaded transonic fan stator[J]. 2012, 27(3). DOI：

摘要

以负荷系数高达0.42的跨声风扇进口级为背景

利用三维数值模拟手段

研究了叶片三维气动造型技术对高负荷跨声风扇静子气动性能的影响

并深入地分析了其影响机理.结果表明:由于激波在静子叶根有垂直于轮毂端壁的趋势

因此前掠造型对于激波/端壁附面层所主导的静子角区分离的控制效果并不明显;相比之下

正弯静子通过加入叶片力使得角区中的低速流体向叶中发生径向迁移

显著地改善了静子的性能;而复合弯掠进一步提高了静子的性能

说明单纯使用前掠造型收效不佳

需要配合正弯造型才能达到最佳效果.

Abstract

Under the background of highly loaded transonic inlet fan stage

which produces loading coefficient of 0.42

three-dimensional(3-D) blading influence on transonic stator aerodynamic performance was analyzed as well as its mechanism with numerical simulation technology.The result indicates that the forward sweep is not effective to control the corner separation conducted by shock/endwall boundary layer interaction because of the trend that the shock always tends to remain perpendicular to the endwall.Positive bow modifies the stator performance obviously through adding the blade force to migrate the low-speed corner fluid toward to mid-span.Sweep/bow composition improves the stator performance further

illustrating that the benefit from pure forward sweep is limited and forward sweep can attain optimum effect when combining the positive bow.

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Related Institution

School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

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Aeroengine Numerical Simulation Research Center,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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