US 12,030,261 B2
Turbomachine component comprising a fibrous preform
Julien Schneider, Moissy-Cramayel (FR); and Yanneck Wielhorski, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/299,605
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 2, 2019, PCT No. PCT/FR2019/052872
§ 371(c)(1), (2) Date Jun. 3, 2021,
PCT Pub. No. WO2020/120869, PCT Pub. Date Jun. 18, 2020.
Claims priority of application No. 1872821 (FR), filed on Dec. 13, 2018.
Prior Publication US 2022/0016855 A1, Jan. 20, 2022
Int. Cl. B29C 70/24 (2006.01); B29K 307/04 (2006.01); B29L 31/00 (2006.01); B29L 31/08 (2006.01)
CPC B29C 70/24 (2013.01) [B29K 2307/04 (2013.01); B29L 2031/082 (2013.01); B29L 2031/748 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A turbomachine component made of composite material comprising a fibrous reinforcement formed by a fibrous preform, and a matrix densifying the fibrous reinforcement, said fibrous preform having a three-dimensional weave formed by a plurality of woven strands; wherein, in a shear plane of the component, all or part of the strands present in said shear plane have fibers forming an angle comprised between 10° and 50° with their centerline and wherein said shear plane corresponds to the plane defined by warp and weft directions of the three-dimensional weave, or to the plane defined by the warp direction and a thickness direction of the three-dimensional weave, or to the plane defined by the weft direction and the thickness direction of the three-dimensional weave.