High strength joints in ceramic matrix composite preforms

Patent metadata

Field	Value
Publication number	US-9291060-B2
Application number	US-201314097866-A
Country	US
Kind code	B2
Filing date	Dec 5, 2013
Priority date	Mar 14, 2013
Publication date	Mar 22, 2016
Grant date	Mar 22, 2016

Abstract

A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.

First claim

What is claimed is:

1. An apparatus comprising:
a gas turbine engine component construction suitable for operational use in an operating environment associated with a gas turbine engine, the component construction including a first ceramic matrix composite preform component comprising a first end surface and a second ceramic matrix composite preform component comprising a second end surface, the first composite preform component including a plurality of extended fibers having an extended portion that protrudes away from the first end surface, the extended fibers received within an internal space of a body of the second composite preform component such that the body of the second composite preform component at least partially envelopes the extended portion of the plurality of extended fibers and creates a joint between the first composite preform component and the second composite preform component at an interface of the first end surface and the second end surface; and wherein the extended fibers are woven into the first ceramic matrix composite preform but not woven into the second ceramic matrix composite preform.

2. The apparatus of claim 1 , wherein the gas turbine engine component construction is a precursor to a ceramic matrix composite component structured for use as an airfoil member in the gas turbine engine.

3. The apparatus of claim 1 , wherein the first composite preform component includes a plurality of body fibers, and wherein the extended fibers protrude only partially into the body of the second composite preform component.

4. The apparatus of claim 1 , wherein the first preform component, the second preform component, and the plurality of extended fibers comprise at least one material selected from the group consisting of glass, carbon, aramid, ceramic oxide, ceramic nitride, and ceramic carbide; and wherein the first preform component and the second preform component comprise a matrix comprising at least one material selected from the group consisting of polymers, metals, silicon carbide, and silicon/silicon carbide.

5. The apparatus of claim 1 , wherein the first composite preform component includes a set of fibers in addition to the extended fibers, the set of fibers less stiff than the extended fibers such that the set of fibers yields its form when the second composite preform component at least partially envelopes the extended portion of the plurality of extended fibers.

6. The apparatus of claim 1 , wherein the second composite preform component includes interstitial spacing between a plurality of internal spaces that matches a spacing of the extended fibers from the first composite preform component.

7. The apparatus of claim 1 , further comprising a laminate strip configured to be applied to the joint.

8. The apparatus of claim 1 , wherein the second composite preform component further comprises a plurality of interwoven fibers, and wherein the plurality of extended fibers have sufficient rigidity to act independently from the plurality of interwoven fibers when received into the internal space of a the body of the second composite preform component.

9. The apparatus of claim 1 , wherein the plurality of extended fibers comprises an outer coating.

10. The apparatus of claim 1 , wherein the second end surface comprises a plurality of interstitial openings configured to receive the plurality of extended fibers.

11. An apparatus comprising:
a gas turbine engine ceramic matrix composite component for a gas turbine engine, comprising a first ceramic preform comprising a first end surface and a second ceramic preform comprising a second end surface,
wherein the first ceramic preform includes a plurality of first extended fibers having an extended portion that protrudes away from the first end surface, the first extended fibers being received within an internal space of a body of the second ceramic preform, and wherein the first extended fibers are woven into the first ceramic preform but not woven into the second ceramic preform;
wherein the second ceramic preform includes a plurality of second extended fibers having an extended portion that protrudes away from the second end surface, the second extended fibers being received within an internal space of a body of the first ceramic preform, and wherein the second extended fibers are woven into the second ceramic preform but not woven into the first ceramic preform; and
wherein an interface of the first end surface and the second end surface forms a joint between the first ceramic preform and the second ceramic preform.

12. The apparatus of claim 11 , wherein the second end surface comprises a plurality of interstitial openings configured to receive the plurality of first extended fibers and the first end surface comprises a plurality of interstitial openings configured to receive the plurality of second extended fibers.

13. The apparatus of claim 11 , further comprising a third ceramic preform positioned within the joint, wherein a portion of at least one of the plurality of first extended fibers and the plurality of second extended fibers extend through the third ceramic preform.

14. The apparatus of claim 13 , wherein the third ceramic preform extends outwardly from a plane occupied by the first ceramic preform and the second ceramic preform.

15. The apparatus of claim 14 , wherein the third ceramic preform has a cross-sectional shape of an airfoil.

16. An apparatus comprising:
a gas turbine engine ceramic matrix composite component, comprising a first ceramic preform arranged along a first longitudinal axis and comprising a first end surface and a plurality of extended fibers having an extended portion that protrudes away from the first end surface, and a second ceramic preform arranged along a second longitudinal axis and comprising a second end surface,
wherein the extended fibers are received within an internal space of a body of the second ceramic preform, wherein a joint is created between the first ceramic preform and the second ceramic preform at an interface of the first end surface and the second end surface, and wherein the extended fibers are woven into the first ceramic preform, but not woven into the body of the second ceramic preform; and
wherein the first longitudinal axis passes through the first end surface and the second longitudinal axis passes through the second end surface.

17. The apparatus of claim 16 , wherein the joint is configured such that first longitudinal axis and the second longitudinal axis occupy a common plane.

18. The apparatus of claim 16 , wherein the joint is configured such that the first longitudinal axis occupies a first plane and the second longitudinal axis occupies a second plane which is skewed from the first plane.

19. The apparatus of claim 16 , wherein the joint is configured such that the first longitudinal axis occupies a first plane and the second longitudinal axis occupies a second plane distinct from the first plane and parallel to the first plane.

Assignees

• Rolls Royce Corp

Inventors

• Lazur Andrew Joseph

Classifications

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F05D2230/23

  by permanently joining parts together · CPC title

• B32B37/14

  characterised by the properties of the layers · CPC title

• Y10T428/2414

  including fringe · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title