发明授权
- 专利标题: Turbomachine vane with integrated metal leading edge and method for obtaining it
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申请号: US16879171申请日: 2020-05-20
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公开(公告)号: US11333028B2公开(公告)日: 2022-05-17
- 发明人: Sébastien Serge Francis Congratel , Célia Iglesias Cano , Antoine Hubert Marie Jean Masson
- 申请人: SAFRAN AIRCRAFT ENGINES
- 申请人地址: FR Paris
- 专利权人: SAFRAN AIRCRAFT ENGINES
- 当前专利权人: SAFRAN AIRCRAFT ENGINES
- 当前专利权人地址: FR Paris
- 代理机构: Pillsbury Winthrop Shaw Pittman LLP
- 优先权: FR1905301 20190521
- 主分类号: F01D5/28
- IPC分类号: F01D5/28 ; B29C33/12 ; F01D5/14 ; B29D99/00
摘要:
A turbomachine vane includes a blading made of composite material with fibrous reinforcement densified by a matrix and an integrated metal leading edge, the blading extending in a longitudinal direction, the leading edge being formed by a metal foil overmolded onto the blading, the foil having a lower wing and an upper wing which extend respectively on the lower and upper faces of the blading while matching an aerodynamic profile of the vane. One of the lower wing and the upper wing has a positioning portion extending in the longitudinal direction, the portion having a flat inner face and an increasing thickness away from the leading edge, and being housed in a correspondingly shaped groove in the blading.
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