Method for manufacturing a composite material part comprising a body extended by a reinforced attachment end
US-11141938-B2 · Oct 12, 2021 · US
Method for producing a bladed component for an aircraft turbine engine
US12583147B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-12583147-B2 |
| Application number | US-202218717869-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 6, 2022 |
| Priority date | Dec 9, 2021 |
| Publication date | Mar 24, 2026 |
| Grant date | Mar 24, 2026 |
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- Title
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Abstract
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A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising including a blade which has a stacking axis and at least one longitudinal end of which is connected to a transverse platform, the method including the steps of: a) producing a fibrous preform, this preform including a first part that is intended to form a blade and at least one second part that is intended to form a platform, this second part of the preform including a disconnect that defines two stacked portions that are separated by a disconnect surface that is substantially parallel to the axis, b) folding the portions, respectively, on two opposing sides of the first part, and c) stiffening the preform.
First claim
Opening claim text (preview).
The invention claimed is: 1 . A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising a blade having a stacking axis and having at least one longitudinal end connected to a transverse platform, the method comprising the steps of: a) producing a fibrous preform, the preform having a generally elongate shape along said axis and being flat, the preform comprising a first part that is intended to form the blade and at least one second part which is situated at a longitudinal end of the preform and which is intended to form the transverse platform, the second part of the preform comprising a disconnect defining two superimposed portions separated by a disconnect surface substantially parallel to the axis, b) folding the portions respectively on two opposite sides of the first part, and c) stiffening the preform, wherein, in step a), the disconnect is such that the portions are connected together, at a junction between the first and second parts, by a connecting line which has a generally undulating shape. 2 . The method according to claim 1 , wherein the connecting line comprises at least one or three undulation antinodes. 3 . The method according to claim 1 , wherein step a) is carried-out by three-dimensional weaving of fibers forming weft threads and warp threads, the warp threads extending along the axis and the weft threads extending perpendicularly to the axis, the weft threads extending continuously in the first part and extending discontinuously in the second part and being interrupted at said disconnect surface. 4 . The method according to claim 3 , wherein step c) is carried out by injecting resin into the preform and polymerizing the resin. 5 . The method according to claim 1 , wherein step a) is carried out by stacking fiber mats, the fiber mats extending along the axis. 6 . The method according to claim 5 , wherein step c) is carried out by thermocompression of the preform, the fibers of which are previously impregnated with a resin. 7 . The method according to claim 1 , wherein the connecting line has an amplitude (T 1 , T 2 ) of between 2 and 20 mm. 8 . The method according to claim 1 , wherein the method comprises, between steps b) and c), a step of forming the preform. 9 . The method according to claim 1 , wherein the method comprises a subsequent step d) of forming the platform, either by mounting and attaching elements to the portions, or by overmolding the portions. 10 . The method according to claim 1 , wherein the connecting line has an amplitude (T 1 , T 2 ) of between 5 and 10 mm.
Assignees
Inventors
Classifications
Three-dimensional woven fabrics · CPC title
Producing blades or the like, e.g. blades for turbines, propellers, or wings · CPC title
Fastening of diaphragms or stator-rings · CPC title
Platforms for stationary or moving blades · CPC title
using blades (F01D5/148 takes precedence) · CPC title
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- What does patent US12583147B2 cover?
- A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising including a blade which has a stacking axis and at least one longitudinal end of which is connected to a transverse platform, the method including the steps of: a) producing a fibrous preform, this preform including a first part that is intended to form a blade and at least one second part…
- Who is the assignee on this patent?
- Safran
- What technology area does this patent fall under?
- Primary CPC classification B29B11/14. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Mar 24 2026 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).