Composite structure

Patent metadata

Field	Value
Publication number	US-10906267-B2
Application number	US-201715804179-A
Country	US
Kind code	B2
Filing date	Nov 6, 2017
Priority date	Nov 4, 2016
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A method of manufacturing a composite component comprises forming a core, surrounding the circumference of the core with a first layer of fabric, applying a second layer of fabric having a different coefficient of thermal expansion from the first layer such that the second layer extends around at least a portion of the circumference of the core and curing the component such that the second layer imparts a compressive or tensile force on the core.

First claim

The invention claimed is:

1. A composite component comprising:
a central region; and
a shell surrounding the central region, wherein the shell comprises
a first layer of fabric; and
a second layer of fabric separate from the first layer of fabric, the first layer of fabric extending around the entire circumference of the central region and the second layer of fabric extending around at least a portion of the circumference of the central region,
wherein the second layer of fabric includes a ply of material forming at least part of said fabric of the second layer of fabric having a different coefficient of thermal expansion from said fabric of the first layer of fabric such that the second layer of fabric imparts a compressive or tensile force on the central region.

2. The composite component of claim 1 , wherein said ply forming at least part of said fabric of the second layer of fabric comprises fibres aligned at an angle relative to fibres in the first layer of fabric forming at least part of said fabric of the first layer of fabric.

3. The composite component of claim 1 , wherein said ply forming at least part of said fabric of the second layer of fabric comprises fibres of a different material from fibres in the first layer forming at least part of said fabric of the first layer of fabric.

4. The composite component claim 1 wherein the second layer includes at least two of said plies forming at least part of said fabric of the second layer of fabric, at least one of said plies having a different coefficients of thermal expansion to one another of said plies.

5. The composite component of claim 1 , wherein the second layer of fabric extends around only a portion of the circumference of the central region.

6. The composite component of claim 1 , wherein the first layer of fabric is positioned between the second layer of fabric and the central region.

7. The composite component of claim 1 , wherein the second layer fabric is positioned between the first layer of fabric and the central region.

8. The composite component of claim 1 , wherein said ply of material forming at least part of said fabric of the second layer of fabric is one of a plurality of plies of material forming at least part of said fabric of the second layer of fabric, wherein an outer ply of the plurality of plies extends over an inner ply of the plurality of plies such that it covers an edge of the inner ply.

9. The composite component of claim 1 , wherein the central region comprises a core.

10. The composite component of claim 1 , wherein at least one of:
the first layer of fabric comprises carbon fibres forming at least part of said fabric of said first layer of fabric and a matrix material, and
the second layer of fabric comprises carbon fibres forming at least part of said fabric of said layer of fabric and a matrix material; wherein the matrix material is a thermosetting resin.

11. The composite component of claim 1 , wherein the composite component is an airfoil structure having:
a leading edge and a trailing edge, the second layer of fabric extending around at least one of the leading edge and trailing edge; and/or
a pressure side and a suction side, wherein the second layer of fabric extends along a portion of the pressure side and/or suction side.

12. The composite component of claim 1 , further comprising a third layer extending around a different portion of the circumference of the central region than the second layer such that it imparts a compressive force on the central region.

13. The composite component of claim 12 , wherein the composite component is an airfoil structure having a leading edge and a trailing edge, wherein the second layer extends around the leading edge and the third layer extends around the trailing edge of the airfoil structure.

14. The composite component of claim 1 , further comprising an outer layer surrounding the first and second layers such that the second layer is positioned between the first layer and the outer layer, wherein the outer layer extends around the entire circumference of the central region.

Assignees

• Ratier Figeac Sas

Inventors

• Amat Pascal
• Grimal Stéphane

Classifications

• B29D99/0003

  Producing profiled members, e.g. beams · CPC title

• B32B5/26

  another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} · CPC title

• B32B5/08 Primary

  the fibres or filaments of a layer being of different substances {, e.g. conjugate fibres, mixture of different fibres} · CPC title

• B32B3/12

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title

• B32B1/08

  Tubular products · CPC title