Method of manufacturing ceramic matrix composite objects

Patent metadata

Field	Value
Publication number	US-10556831-B2
Application number	US-201415033717-A
Country	US
Kind code	B2
Filing date	Oct 29, 2014
Priority date	Nov 1, 2013
Publication date	Feb 11, 2020
Grant date	Feb 11, 2020

Abstract

A method of manufacturing ceramic matrix composite objects is disclosed. The method comprises the steps of providing first and second substantially two dimensional arrangements of one or more fiber plies, and machining the first and second arrangements to predetermined configurations to form first and second preforms. The second preform is made to conform to a surface of the first preform such that at least some of the fibers of the second preform are orientated at least partially in a plane outside that defined by the fibers of the first preform, and fixed to the first preform to form a combined first and second preform. The combined first and second preform is rigidized. Ceramic matrix composite objects manufactured by this method are also disclosed.

First claim

The invention claimed is:

1. A method of manufacturing a ceramic matrix composite object comprising the steps of:
(i) providing a first arrangement of one or more fibre plies, and machining the first arrangement to a predetermined configuration to form a first preform;
(ii) providing a second arrangement of one or more fibre plies, and machining the second arrangement to a predetermined configuration to form a second preform;
(iii) wrapping the second preform around at least one edge of the first preform;
(iv) fixing the first and second preforms together to form a combined first and second preform;
(v) providing one or more further arrangements of one or more fibre plies, machining the one or more further arrangements to a predetermined configuration to form one or more further preforms; and successively adhering each of the one or more further preforms to the combined first and second preform to form a complete preform in which at least one of the one or more further preforms are wrapped around one of the first, second, or one or more further preforms; and
(vi) rigidizing the complete preform by a step comprising infiltrating the combined first and second preforms with a liquid material, the liquid material selected to react with a component of the first and second preforms so as to form a ceramic.

2. A method as claimed in claim 1 , wherein the second preform is configured to be flexible.

3. A method as claimed in claim 1 , wherein the ceramic matrix composite is a carbon-silicon carbide ceramic matrix composite.

4. A method as claimed in claim 1 , wherein the step of rigidising the combined first and second preforms comprises pyrolysing the combined first and second preforms.

5. A method as claimed in claim 1 , wherein the step of rigidising the combined first and second preforms comprises increasing the carbon content of the combined first and second preforms using a chemical vapour infiltration process.

6. A method as claimed in claim 1 , wherein the liquid material is liquid silicon.

7. A method as claimed in claim 1 , wherein the step of fixing the second preform to the first preform comprises applying an adhesive to one of the first or second preforms, the adhesive being selected to yield a high carbon content when pyrolysed.

8. A method as claimed in claim 7 , wherein the adhesive is a phenolic- or pitch-based adhesive.

9. A method as claimed in claim 1 , wherein the one or more further preforms are configured to remain flexible.

10. A method as claimed in claim 1 , wherein, in step (iii) at least some of the fibers of the second preform are at least partially oriented in a plane outside that defined by fibers of the first preform.

11. A method as claimed in claim 1 , wherein the ceramic matrix composite object is an aerodynamic fin.

12. A method of manufacturing a ceramic matrix composite object in the shape of an aerodynamic fin, the method comprising the steps of:
(i) providing a first arrangement of one or more fibre plies, and machining the first arrangement to a predetermined configuration to form a first preform;
(ii) providing a second arrangement of one or more fibre plies, and machining the second arrangement to a predetermined configuration to form a second preform;
(iii) wrapping the second preform around at least one edge of the first preform;
(iv) fixing the first and second preforms together to form a combined first and second preform in the shape of an aerodynamic fin; and
(v) rigidising the combined first and second preform.

Assignees

• Mbda Uk Ltd

Inventors

• Ackerman Terence
• Pickford Christopher Peter

Classifications

• C04B2237/086

  Carbon interlayers · CPC title

• C04B35/65

  Reaction sintering of free metal- or free silicon-containing compositions {(C04B35/573, C04B35/591 take precedence)} · CPC title

• C04B2235/614

  Gas infiltration of green bodies or pre-forms · CPC title

• C04B37/008

  by means of an interlayer consisting of an organic adhesive, e.g. phenol resin or pitch · CPC title

• C04B35/64

  Burning or sintering processes (C04B33/32 takes precedence {; powder metallurgy B22F}) · CPC title