IP Library › Granted Patent US 12,270,318
Granted Patent B1
US 12,270,318 · App. 18/835,233 · Granted Apr 8, 2025

Hybrid metal/composite blade with textile orientation adapted to mechanical stresses

Inventors: Pierre-Antoine Bossan (Moissy-Cramayel, FR); François Charleux (Moissy-Cramayel, FR)
Assignee: SAFRAN AIRCRAFT ENGINES
F01D5/282F01D5/147F01D25/005F05D2220/30F05D2240/12F05D2240/30F05D2300/603
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Quick Facts
Patent No.
US 12,270,318
App. No.
18/835,233
Granted
Apr 8, 2025
Kind
B1
Abstract

A blade made of a composite material, the blade including a fibrous reinforcement densified by an organic matrix and being provided, in an attachment zone, with a metal element, wherein the reinforcement includes, in at least one region of the attachment zone, a surface textile orientation adapted to the direction of mechanical stresses by having first skin threads that extend in a main mechanical stress direction and that are bonded to second skin threads transverse to the first threads, the first skin threads making up most of the surface area of the region of the attachment zone.

Claims (12)

1. A blade or vane made of a composite material, the blade or vane comprising:

a fibrous reinforcement densified by an organic matrix and comprising a skin and a core,

a metal element attached to the fibrous reinforcement on an attachment zone of the skin;

wherein the reinforcement comprises, in at least one region of the attachment zone, a surface textile orientation adapted to the direction of mechanical stresses by having first skin threads that extend in a main mechanical stress direction and that are bonded to second skin threads transverse to the first threads, said first skin threads being a majority of all the threads on the surface of said region of the attachment zone, and wherein a textile orientation of the core is different than the surface textile orientation;

wherein:

the metal element is a protective foil covering a leading edge of the blade or vane, and the main mechanical stress direction corresponding to an axial direction of the blade or vane which corresponds to a chord of the blade or vane, or

the blade or vane being a blade and defining an internal cavity and the metal element being a spar inserted in this internal cavity, the spar defining a root intended to be fixed to a rotating disk, the main mechanical stress direction corresponding to a radial direction of the blade which corresponds to an axis joining the root to a top of the blade.

2. The blade or vane according to claim 1 , wherein a proportion of the first skin threads on the surface is at least equal to twice a proportion of the second skin threads on the surface in said at least one region of the attachment zone.

3. The blade or vane according to claim 1 , where the fibrous reinforcement is woven by having, at least in the skin, an evolving weave between the at least one region of the attachment zone and a zone of the blade located outside the attachment zone.

4. The blade or vane according to claim 1 , wherein the at least one region of the attachment zone comprises a first region with a first proportion of first surface threads, and a second region, distinct from the first region, with a second proportion of first surface threads, distinct from the first proportion.

5. The blade or vane according to claim 1 being a fan blade and wherein the metal element is the protective foil.

6. The blade or vane according to claim 1 being an outlet guide blade and wherein the metal element is the protective foil.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Aug 1, 2024
From: BOSSAN, PIERRE-ANTOINE; CHARLEUX, FRANÇOIS
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 068156/0534 →
Priority Claims (1)
FR 2200933 · Feb 2, 2022 · national
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