US 12,091,986 B2
Vane comprising a structure made of composite material, and associated manufacturing method
Vincent Joudon, Moissy-Cramayel (FR); Clément Cottet, Moissy-Cramayel (FR); Vivien Mickaël Courtier, Moissy-Cramayel (FR); and Régis Eugène Henri Servant, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/285,122
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Mar. 24, 2022, PCT No. PCT/FR2022/050549
§ 371(c)(1), (2) Date Sep. 29, 2023,
PCT Pub. No. WO2022/208002, PCT Pub. Date Oct. 6, 2022.
Claims priority of application No. 2103278 (FR), filed on Mar. 30, 2021.
Prior Publication US 2024/0175363 A1, May 30, 2024
Int. Cl. F01D 5/14 (2006.01); F01D 5/28 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/141 (2013.01); F01D 5/282 (2013.01); F05D 2220/36 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A blade of a turbomachine comprising:
a structure with an aerodynamic profile comprising two facing skins, the skins comprising a fibrous reinforcement densified by a matrix; and
a spar comprising a blade root portion configured to be mounted on a hub of a rotor of the turbomachine, an airfoil portion disposed inside the structure with aerodynamic profile between the two skins, and a stilt portion extending outside the structure with aerodynamic profile between the blade root portion and the airfoil portion, wherein the airfoil portion comprises a body connected to the blade root portion and two branches extending radially from the body; and a structural reinforcement extending from the blade root portion to the body of the airfoil portion, the structural reinforcement being secured to the blade root portion and configured to form a force path distinct from the stilt portion in an event of rupture of the spar within the stilt portion.