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发表时间：2022-10-09

发表刊物：工程热物理学报

卷号：39

期号：5

页面范围：977-984

ISSN号：0253-231X

摘要：This paper investigates the influence of asymmetric boundary layer
   suction through endwall holes on aerodynamic performance in large
   turning angle compressor cascades. Numerical methods verified by
   experiment, the suction position located at endwall near suction
   surface, four suction schemes are divided along the chord length of the
   cascades, the calculating domain includes cavity. Results show the
   boundary layer suction on endwall that cover separation point could
   improve the corner flow condition of the suction side, delay flow
   separation and reduce losses. But adverse effects arise on corner of the
   other side without suction, such as earlier flow separation and larger
   range of corner separation.

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