叶片设计方法、叶片、压气机和航空发动机

By considering the influence of blade height section and inlet boundary layer thickness in blade design, and optimizing the relationship between blade thickness and radius, the problem of poor blade aerodynamic performance in the prior art is solved, and better aerodynamic performance and structural reliability are achieved.

CN115982919BActive Publication Date: 2026-07-17AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
Filing Date
2021-10-14
Publication Date
2026-07-17

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Abstract

本公开涉及压气机叶片设计领域，特别涉及一种叶片设计方法、叶片、压气机和航空发动机。其中方法包括：基于叶片的不同叶高截面的最大厚度Dmaxi(为xi和 / 或A的函数)、最大厚度位置Lmaxi(为xi和 / 或B的函数)、前缘半径RLi(为xi的函数)和后缘半径RTi(为xi的函数)中的至少之一，确定不同叶高截面的厚度分布；和基于所确定的不同叶高截面的厚度分布，生成叶片；其中，xi＝(Ri‑Rh1) / (Rt1‑Rh1)，Ri为不同叶高截面的几何半径，Rh1为叶片的内径，Rt1为叶片的外径；A和B为根据压气机的进口附面层厚度确定的常数。基于此，方便设计得到性能更好的压气机叶片。
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