Method of manufacturing a composite component

Patent metadata

Field	Value
Publication number	US-10807322-B2
Application number	US-201615568354-A
Country	US
Kind code	B2
Filing date	Apr 25, 2016
Priority date	Apr 30, 2015
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

There is disclosed a method of manufacturing a composite component comprising a main body and an integral flange, the method comprising: applying fibre reinforcement material on a tool having a main body portion and a flange-forming portion to provide a pre-form having first, second and third contiguous regions, the first region corresponding to the main body of the component and the second region corresponding to the integral flange of the component; and causing relative movement between the flange-forming portion and the main body portion so that the second region of the pre-form deforms to form the flange; wherein the relative movement of the flange-forming portion and the main body portion causes sliding movement between the second and third regions of the pre-form and the flange-forming, thereby producing a tension force in at least the second region of the pre-form during forming of the flange.

First claim

The invention claimed is:

1. A method of manufacturing a composite component comprising a main body and an integral flange, the method comprising:
applying fibre reinforcement material on a tool having a main body portion and a flange-forming portion to provide a pre-form having first, second and third contiguous regions, the first region corresponding to the main body of the component and the second region corresponding to the integral flange of the component, wherein the thickness of the third region of the pre-form is less than the thickness of the second region of the pre-form; and
causing relative movement between the flange-forming portion and the main body portion so that the second region of the pre-form deforms to form the flange, wherein the relative movement of the flange-forming portion and the main body portion causes sliding movement between (i) the second region and the flange-forming portion and (ii) between the third region and the flange-forming portion, thereby producing a tension force in at least the second region of the pre-form during forming of the flange; and
removing the third region of the pre-form.

2. A method according to claim 1 , further comprising separating a part of the composite material formed on the tool after the forming operation including material corresponding to the third region of the pre-form.

3. A method according to claim 1 , wherein the third region of the pre-form comprises fewer layers of fibre reinforcement material than the second region of the pre-form.

4. A method according to claim 1 , wherein the thickness of the third region of the pre-form is 50% or less of the thickness of the second region of the pre-form.

5. A method according to claim 1 , wherein the fibre reinforcement material is applied on the tool so that the thickness of the second region of the preform is substantially constant, and so that the thickness of the third region of the pre-form is substantially constant.

6. A method according to claim 1 , wherein the preform comprises a base-ply set of fibre reinforcement material extending through at least the second and third regions of the pre-form, and an upper-ply set extending through at least the second region but not the third region of the pre-form.

7. A method according to claim 6 , wherein the base-ply set comprises at least one layer of fibre reinforcement material, and wherein the upper-ply set comprises a plurality of layers of fibre-reinforcement material.

8. A method according to claim 1 , further comprising inhibiting sliding movement between the first region of the pre-form and the main body portion of the tool.

9. A method according to claim 1 , wherein the fibre reinforcement material is applied on the tool so that the third region of the pre-form has an area of at least 25% of the area of the second region of the pre-form.

10. A method according to claim 1 , wherein the fibre reinforcement material is applied so that the first, second and third regions are contiguous along a generally longitudinal direction, and wherein the third region of the pre-form has a longitudinal extent of at least 25% of the longitudinal extent of the second region of the pre-form.

11. A method according to claim 1 , wherein the flange-forming portion of the tool has a lay-up surface that is substantially continuous with a lay-up surface of the main body portion of the tool in a lay-up configuration of the tool, and a side surface which extends between the lay-up surfaces of the flange-forming portion and main body portion of the tool in a forming configuration of the tool.

12. A method according to claim 1 , wherein the direction of relative movement of the flange-forming portion and main body portion of the tool is parallel to the extent of the flange.

13. A method according to claim 1 , wherein the composite component is an annular or a partially annular component, such as a casing for a gas turbine engine, wherein the main body portion and the flange-forming portions of the tool are configured for relative radial movement, and wherein the flange is a radial flange.

Assignees

• Rolls Royce Plc

Inventors

• Marengo Giovanni Antonio

Classifications

• B29L2031/7504

  Turbines · CPC title

• B29C48/76

  Venting {, drying} means; Degassing means · CPC title

• B29C70/56

  Tensioning reinforcements before or during shaping · CPC title

• B29C70/462 Primary

  Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames · CPC title