公开(公告)号：US11898466B2

公开(公告)日：2024-02-13

申请号：US17619505

申请日：2020-06-18

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Célia Iglesias Cano ,  Vincent Marie Jacques Rémi De Carné-Carnavalet ,  Antoine Hubert Marie Jean Masson

IPC分类号： F01D9/04 ,  F01D5/28

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.

公开(公告)号：US12037922B2

公开(公告)日：2024-07-16

申请号：US18009881

申请日：2021-06-15

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Azalia Moradi ,  Bassem Ben Belgacem ,  Célia Iglesias Cano

IPC分类号： F01D5/28 ,  B29C70/22 ,  B29C70/34 ,  B29C70/86 ,  B29K307/04 ,  B29K705/00 ,  B29L31/08 ,  F01D5/00 ,  F01D5/14

CPC分类号： F01D5/282 ,  B29C70/222 ,  B29C70/34 ,  B29C70/86 ,  F01D5/005 ,  F01D5/147 ,  B29K2307/04 ,  B29K2705/00 ,  B29L2031/082 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/80 ,  F05D2240/30

摘要： A turbomachine blade includes a blading made of composite material with a fibrous reinforcement densified by a matrix and a metal leading edge formed by a metal foil, the foil having an intrados fin and an extrados fin which extend respectively over intrados and extrados faces of the blading by conforming to an airfoil of the blade, wherein the blade also includes at least one unidirectional fabric ply made of composite material on the leading edge between the blading and the metal foil, each unidirectional fabric ply extending at least partially over the intrados and extrados faces of the blading.

公开(公告)号：US11333028B2

公开(公告)日：2022-05-17

申请号：US16879171

申请日：2020-05-20

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Sébastien Serge Francis Congratel ,  Célia Iglesias Cano ,  Antoine Hubert Marie Jean Masson

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.