Rapid processing of laminar composite components
US-12180120-B2 · Dec 31, 2024 · US
Composite aerofoil vane
US9670788B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9670788-B2 |
| Application number | US-201414185390-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 20, 2014 |
| Priority date | Mar 21, 2013 |
| Publication date | Jun 6, 2017 |
| Grant date | Jun 6, 2017 |
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- Title
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Abstract
Official abstract text for this publication.
A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.
First claim
Opening claim text (preview).
The invention claimed is: 1. A composite aerofoil vane for a gas turbine engine, the vane in use extending in a generally radial direction across an axially- and circumferentially-extending annular duct, the duct in use carrying a gas flow, the vane comprising: a plurality of first reinforcing fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions, the second fibres being interlaced with the first fibres, wherein at least some of the second fibres are interlaced with at least some of the first fibres so as to extend through the whole circumferential thickness of the vane. 2. The vane of claim 1 , in which the second fibres are arranged to substantially define the aerofoil surface of the vane and to provide a gas-washed surface. 3. The vane of claim 1 , in which at least some of the second fibres are interlaced with at least some of the first fibres so as to not extend through the whole circumferential thickness of the vane. 4. The vane of claim 1 , in which the first fibres comprise generally radially-extending bundles, tows or structures. 5. The vane of claim 1 , in which the first fibres comprise generally radially-extending hollow structures. 6. The vane of claim 1 , further comprising a surface layer outward of the second fibres. 7. The vane of claim 6 , in which the surface layer comprises fibres. 8. The vane of claim 7 , in which the surface layer comprises a fine, thin woven or braided fabric or matting. 9. The vane of claim 6 , in which the surface layer is wrapped around the vane.
Assignees
Inventors
Classifications
Fibres · CPC title
using blades (F01D5/148 takes precedence) · CPC title
especially adapted for elastic fluid pumps · CPC title
Composites; e.g. fibre-reinforced · CPC title
Selecting particular materials · CPC title
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- What does patent US9670788B2 cover?
- A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are inter…
- Who is the assignee on this patent?
- Rolls Royce Plc
- What technology area does this patent fall under?
- Primary CPC classification F01D5/282. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jun 06 2017 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).