US 11,933,194 B2
Fan or propeller vane for an aircraft turbomachine and method for manufacturing same
Vivien Mickael Courtier, Moissy-Cramayel (FR); Teddy Fixy, Moissy-Cramayel (FR); Clement Pierre Postec, Moissy-Cramayel (FR); and Eddy Keomorakott Souryavongsa, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/757,348
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 17, 2020, PCT No. PCT/FR2020/052514
§ 371(c)(1), (2) Date Jun. 14, 2022,
PCT Pub. No. WO2021/123652, PCT Pub. Date Jun. 24, 2021.
Claims priority of application No. 1915318 (FR), filed on Dec. 20, 2019.
Prior Publication US 2023/0010778 A1, Jan. 12, 2023
Int. Cl. F01D 5/28 (2006.01); B29C 70/24 (2006.01); B29C 70/48 (2006.01); F01D 5/14 (2006.01); B29L 31/08 (2006.01)
CPC F01D 5/282 (2013.01) [B29C 70/24 (2013.01); B29C 70/48 (2013.01); F01D 5/147 (2013.01); B29L 2031/082 (2013.01); F05D 2300/6012 (2013.01); F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A fan or propeller vane for an aircraft turbomachine, the vane being made from composite material and comprising a blade and a root, the root being formed by a longitudinal end of a spar which is formed by a fibrous reinforcement formed of three-dimensionally woven threads and a portion of which extends inside the blade, said blade having an aerodynamic profile defined by a skin formed by woven threads and surrounding said portion of the spar, the spar and the skin being embedded in a polymerized resin, wherein said portion of the spar comprises protruding longitudinal stiffeners which delimit between them spaces for housing longitudinal inserts formed from a cellular material.