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公开(公告)号：US11898466B2
公开(公告)日：2024-02-13
申请号：US17619505
申请日：2020-06-18
发明人： Célia Iglesias Cano , Vincent Marie Jacques Rémi De Carné-Carnavalet , Antoine Hubert Marie Jean Masson
CPC分类号： F01D9/041 , F01D5/282 , F01D5/288 , F05D2230/31 , F05D2230/90 , F05D2240/121 , F05D2240/122
摘要： A method for coating a turbomachine guide vane including a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, the method including completely covering one of the faces of the vane with a polymer coating of thickness (e1) provided with grooves, removing the grooves from a part of the polymer coating in such a way that the polymer coating includes a grooved zone and a non-grooved zone, coating the non-grooved zone with a coat of paint of thickness (e3) such that the thickness of the coat of paint superimposed on the non-grooved zone is substantially equal to the thickness (e1) of the grooved zone.
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公开(公告)号：US11795836B2
公开(公告)日：2023-10-24
申请号：US17996024
申请日：2021-04-12
申请人： SAFRAN
IPC分类号： F01D25/00 , B29C45/14 , B29C45/16 , F01D9/04 , B29K307/04 , B29K705/08 , B29L31/08 , B29C64/147 , B29C70/02 , B29C70/08 , B29C64/205 , B29C70/20 , B29C70/88
CPC分类号： F01D25/005 , B29C45/14336 , B29C45/14631 , B29C45/1671 , F01D9/041 , B29C64/147 , B29C64/205 , B29C70/021 , B29C70/08 , B29C70/085 , B29C70/202 , B29C70/885 , B29K2307/04 , B29K2705/08 , B29L2031/082 , F05D2220/323 , F05D2230/21 , F05D2240/12 , F05D2240/123 , F05D2300/6032 , F05D2300/6034 , F05D2300/615
摘要： A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.
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公开(公告)号：US11333028B2
公开(公告)日：2022-05-17
申请号：US16879171
申请日：2020-05-20
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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