US 11,788,420 B2
Fan blade comprising an insert of stiff fibers
Guillaume Pascal Jean-Charles Gondre, Moissy-Cramayel (FR); and Thomas Alain De Gaillard, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/909,175
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Mar. 3, 2021, PCT No. PCT/FR2021/050358
§ 371(c)(1), (2) Date Sep. 2, 2022,
PCT Pub. No. WO2021/176179, PCT Pub. Date Sep. 10, 2021.
Claims priority of application No. 2002126 (FR), filed on Mar. 3, 2020.
Prior Publication US 2023/0088650 A1, Mar. 23, 2023
Int. Cl. F01D 5/28 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/282 (2013.01) [F01D 5/147 (2013.01); F05D 2220/32 (2013.01); F05D 2240/30 (2013.01); F05D 2300/6034 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A fan blade of a turbomachine comprising a composite material structure comprising a fibrous reinforcement obtained by three-dimensional weaving of warp strands and weft strands and a matrix in which the fibrous reinforcement is embedded;
wherein the composite material structure comprises a leading edge and a trailing edge;
wherein the fibrous reinforcement comprises a first portion forming the trailing edge and a second portion forming the leading edge;
wherein the warp strands comprise first strands having a predefined stiffness
and second strands having a stiffness greater than the stiffness of the first strands and a Young's modulus comprised between 1.2 and 1.5 times a Young's modulus of the first strands; and
wherein the first portion comprises all or part of the first strands and is devoid of second strands and the second portion comprises all or part of the second strands.