Method of reducing burn-on time

Patent metadata

Field	Value
Publication number	US-11059238-B2
Application number	US-201916676606-A
Country	US
Kind code	B2
Filing date	Nov 7, 2019
Priority date	Dec 6, 2018
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

A method of reducing a burn-on time of a composite component including a body comprising a plurality of fibres layered between a front face of the body and a rear face of the body within a matrix material, wherein the body comprises an edge face between the front face and the rear face at least partially formed by edges of the layers of fibres. The method comprising shaping an edge portion of the body in order to control a local concentration of vapours from the matrix material at the edge face of the body, the vapours having been produced during heating of the composite component and having passed between the layers of fibre of the body to the edge face.

First claim

I claim:

1. A method of reducing a burn-on time of a composite component after the composite component has been heated, wherein the composite component comprises a body comprising a plurality of layers of fibres layered between a front face of the body and a rear face of the body within a matrix material, wherein the body comprises an edge face between the front face and the rear face at least partially formed by edges of the layers of fibres, wherein the method comprises:
shaping an edge portion of the body in order to control a local concentration of vapours from the matrix material at the edge face of the body, the vapours having been produced during heating of the composite component and having passed between the layers of fibre of the body to the edge face;
wherein the edge portion is shaped such that positions of the edges of two or more of the layers of fibres are staggered in a direction parallel to the front face of the body, such that at least a portion of the edge face is formed at a non-perpendicular angle relative to the front face; and
wherein the edge portion is shaped such that the edge face has an undulating profile along a length of the edge face through a full thickness of the edge portion, and the edge portion does not face another edge of the body with mating undulations.

2. The method of claim 1 , wherein the edge portion is shaped by machining the edge face after the body of the composite component has been formed.

3. The method of claim 1 , wherein the edge portion is shaped by layering the fibres of the body such that the edges of two or more of the layers of fibres are staggered in a direction parallel to the front face of the body prior to curing the composite component.

4. The method of claim 1 , wherein shaping the edge portion of the body comprises bending or folding the body of the composite component out of a plane of the front face to form a bend portion extending along the edge portion.

5. The method of claim 1 , wherein the method further comprises providing an edge cap extending at least partially over the front face and the rear face, and around the edge face.

6. The method of claim 1 , wherein the method further comprises, installing one or more fasteners passing through the layered fibres of the body, such that the fasteners act to resist separation of the layers of fibres at the edge face.

7. The method of claim 6 , wherein the method further comprises providing a strip of resilient material over the front and/or rear faces of the body, the strip of resilient material extending at least partially along the length of the edge face, wherein the one or more fasteners pass though the strip of resilient material.

8. The method of claim 6 , wherein shaping the edge portion of the body comprises bending or folding the body of the composite component out of a plane of the front face to form a bend portion extending along the edge portion, and the one or more fasteners pass though the body on at least one side of the bend portion.

9. A composite component for a gas turbine engine, the component comprising
a body comprising a plurality of layers of fibres layered between a front face of the body and a rear face of the body within a matrix material, the body comprising an edge face between the front face and the rear face at least partially formed by edges of the layers of fibres, and wherein an edge portion of the body is shaped such that a concentration of vapours from the matrix material at the edge face of the body, that are produced during heating of the composite component and pass between the layers of fibre of the body to the edge face, is reduced,
wherein the positions of the edges of two or more of the layers of fibres are staggered in a direction parallel to the front face of the body, such that at least a portion of the edge face is formed at a non-perpendicular angle relative to the front face, and
wherein the edge portion is shaped such that the edge face has an undulating profile along a length of the edge face through a full thickness of the edge portion, and the edge portion does not face another edge of the body with mating undulations.

10. The composite component of claim 9 , wherein the component further comprises one or more fasteners passing through the layered fibres adjacent to the edge face.

11. The composite component of claim 10 , wherein the component comprises a strip of resilient material provided over the front and/or rear faces of the body, the strip of resilient material extending at least partially along the length of the edge face, wherein the fasteners pass though the strip of resilient material.

12. The composite component of claim 9 , wherein the body comprises a bend portion extending along the length of the edge face, wherein the body bends out of a plane of the front and/or rear face at the bend portion.

13. An assembly for an electrical system for a gas turbine engine, the assembly comprising:
the composite component according to claim 9 ; and
an electrical component coupled to the body.

Assignees

• Rolls Royce Plc

Inventors

• Green Christopher L

Classifications

• B29C70/545 Primary

  Perforating, cutting or machining during or after moulding · CPC title

• B29C70/302

  Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• B29C70/06

  Fibrous reinforcements only · CPC title