US 11,982,209 B2
Vane made of composite material having a three-dimensional woven fibrous reinforcement and two-dimensional woven skin and method for manufacturing same
Clément Pierre Postec, Moissy-Cramayel (FR); Thomas Alain De Gaillard, Moissy-Cramayel (FR); Teddy Fixy, Moissy-Cramayel (FR); and Eddy Keomorakott Souryavongsa, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/010,751
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 9, 2021, PCT No. PCT/FR2021/051035
§ 371(c)(1), (2) Date Dec. 15, 2022,
PCT Pub. No. WO2021/255366, PCT Pub. Date Dec. 23, 2021.
Claims priority of application No. 2006378 (FR), filed on Jun. 18, 2020.
Prior Publication US 2023/0193766 A1, Jun. 22, 2023
Int. Cl. F01D 5/28 (2006.01); B29C 70/22 (2006.01); B29C 70/34 (2006.01); B29C 70/86 (2006.01); B29K 307/04 (2006.01); B29K 705/00 (2006.01); B29L 31/08 (2006.01); F01D 5/00 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/282 (2013.01) [B29C 70/222 (2013.01); B29C 70/34 (2013.01); B29C 70/86 (2013.01); F01D 5/005 (2013.01); F01D 5/147 (2013.01); B29K 2307/04 (2013.01); B29K 2705/00 (2013.01); B29L 2031/082 (2013.01); F05D 2220/32 (2013.01); F05D 2230/23 (2013.01); F05D 2230/80 (2013.01); F05D 2240/30 (2013.01)] 6 Claims
OG exemplary drawing
 
1. A blade for an aircraft gas turbine engine comprising, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge, the blade comprising: a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and an aerofoil body part, wherein the blade further comprises a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core so as to define a thinned leading edge portion, the skin comprising one or more two-dimensional woven plies each wound around a spar of the blade core, the skin further defining the trailing edge of the blade, wherein a filler material is present at least between a distal end of the front edge of the aerofoil body part of the blade core and the skin made of composite material, wherein said filler material extends from the shank to the blade tip, wherein said filler material is a foam or a resin, wherein the blade further comprises a second filler material that is present between a distal end of the rear edge of the aerofoil body part of the blade core and the skin made of composite material, said second filler material extending from the shank to the blade tip and the second filler material being a foam or a resin, and
wherein the ends of each two-dimensional woven ply meet at a suction-side face of the aerofoil body outside the trailing edge, at a position corresponding to 50% or more of a chord length of the blade measured from the leading edge to the trailing edge of the blade.