CMC component including directionally controllable CMC insert and method of fabrication

Patent metadata

Field	Value
Publication number	US-11459908-B2
Application number	US-201816119142-A
Country	US
Kind code	B2
Filing date	Aug 31, 2018
Priority date	Aug 31, 2018
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

A ceramic matrix composite (CMC) component including a plurality of layers of a CMC and a directionally controllable CMC insert. The directionally controllable CMC insert is disposed in the plurality of layers of a ceramic matrix composite. The directionally controllable CMC insert includes an optimized architecture to strengthen a high stress region of the CMC component. The directionally controllable CMC insert is geometrically configured and disposed within the plurality of layers of the CMC to redirect a crack in the CMC component toward a region of low crack growth driving force. A turbomachine and method of forming a turbomachine member including a plurality of layers of a CMC and having the directionally controllable CMC insert disposed in a shaped void are additionally disclosed.

First claim

What is claimed is:

1. A ceramic matrix composite (CMC) component comprising:
a plurality of CMC layers, at least one of the plurality of CMC layers defining a first plane; and
a CMC insert disposed in the plurality of CMC layers, the CMC insert comprising:
a plurality of plies, wherein the plurality of plies includes at least a first ply including a first plurality of fibers oriented in a first direction and at least a second ply including a second plurality of fibers oriented in a second direction, the first direction and the second direction defining a third direction that is orthogonal to both the first direction and the second direction; and
a joint interface between the CMC insert and at least one of the plurality of CMC layers, the CMC insert being geometrically configured and disposed within the plurality of CMC layers such that the first plurality of fibers of the at least first ply of the plurality of plies of the CMC insert is oriented in the first plane defined by the at least one of the plurality of CMC layers, wherein the CMC insert comprises a side portion,

wherein the side portion is angled with respect to the first plane and is angled with respect to a second plane that is defined by the third direction and is defined by the first direction or the second direction, and
wherein an architecture of the plurality of plies of the CMC insert is symmetric about a mid-plane of the CMC component, the mid-plane being parallel to the first plane and the mid-plane being between two plies with a substantially identical orientation.

2. The CMC component according to claim 1 , wherein the plurality of CMC layers comprise a shaped void, the CMC insert disposed within the shaped void.

3. The CMC component according to claim 2 , wherein a geometric shape of the CMC insert and a geometric shape of the shaped void are configured within machining tolerances of 50 mils or less.

4. The CMC component according to claim 2 , wherein the shaped void and the CMC insert are geometrically configured to form a mechanical interlocking joint therebetween.

5. The CMC component according to Claim 1 , wherein the first plane defines a shape of the CMC insert, the shape being at least one of a dovetail shape or a keyhole shape.

6. The CMC component according to claim 1 , wherein the CMC component comprises one of a combustor liner, a shroud, a turbine center frame, a turbine blade, or a turbine vane.

7. The CMC component according to claim 1 , wherein the plurality of plies of the CMC insert includes a top ply and a bottom ply, and wherein the joint interface extends continuously from the bottom ply to the top ply.

8. The CMC component according to claim 1 , wherein the first plane defines a shape of the CMC insert, the shape being tree-shaped such that the shape includes a plurality of stacked isosceles trapezoids comprising non- 90 degree angles between sides, wherein the plurality of stacked isosceles trapezoids progressively decrease in size.

9.
The CMC component according to claim 8 , wherein a third plane that is orthogonal to the first plane defines a second shape of the CMC insert, the second shape being a dovetail shape.

10. A turbomachine comprising:
a CMC component comprised of a plurality of CMC material layers, the CMC component including a shaped void contained therein the plurality of CMC material layers, wherein at least one of the plurality of CMC material layers define a first plane; and
a CMC insert defining a width and a length, the length longer than the width, the CMC insert disposed within the shaped void, the CMC insert including a plurality of plies, wherein the plurality of plies include at least a first ply including a first plurality of fibers oriented in a first direction and at least a second ply including a second plurality of fibers oriented in a second direction, and a joint interface between the CMC insert and the plurality of CMC material layers, wherein the first direction and the second direction define a third direction that is orthogonal to both the first direction and the third direction,
wherein the shaped void and the CMC insert are geometrically configured and oriented with respect to each other such that the first plurality of fibers of the at least first ply of the plurality of plies of the CMC insert is oriented in the first plane with at least one of the plurality of CMC material layers of the CMC component to form a mechanical interlocking joint therebetween, wherein the CMC insert comprises a side portion,
wherein the side portion is angled with respect to the first plane and is angled with respect to a second plane that is defined by the third direction and is defined by the first direction or the second direction and
wherein an architecture of the plurality of plies of the CMC insert is symmetric about a mid-plane of the CMC component, the mid-plane being parallel to the first plane and the mid- plane being between two plies with a substantially identical orientation.

11. The turbomachine according to claim 10 , wherein the first plane defines a shape of the CMC insert, the shape being at least one of a dovetail shape or a keyhole shape.

12. The turbomachine according to claim 10 , wherein the CMC component comprises one of a combustor liner, a shroud, a turbine center frame, a turbine blade or a turbine vane.

13. The turbomachine of claim 10 , wherein the first plane defines a shape of the CMC insert, the shape being tree-shaped such that the shape includes a plurality of stacked isosceles trapezoids comprising non-90 degree angles between sides, wherein the plurality of stacked isosceles trapezoids progressively decrease in size.

14.
The turbomachine of claim 13 , wherein a third plane that is orthogonal to the first plane defines a second shape of the CMC insert, the second shape being a dovetail shape.

15. A method of forming a turbomachine member, the method comprising:
forming a shaped void in a portion of a plurality of CMC material layers in a shape, wherein at least one of the plurality of CMC material layers defines a first plane; and
disposing a CMC insert into the shaped void formed in the plurality of CMC material layers, the CMC insert including a plurality of plies, wherein the plurality of plies includes at least a first ply including a first plurality of fibers oriented in a first direction, and at least a second ply including a second plurality of fibers oriented in a second direction, wherein the CMC insert is geometrically shaped to form a joint interface with the shaped void, wherein the first direction and the second direction define a third direction that is orthogonal to both the first direction and the third direction,
wherein the CMC insert is geometrically configured and disposed within the turbomachine member such that the first plurality of fibers of the first ply of the plurality of plies of the CMC insert is oriented in the first plane with at least one of the plurality of CMC material layers,
wherein the CMC insert comprises a side portion, wherein the side portion is angled with respect to the first plane and is angled with respect to a second plane that is defined by the third direction and is defined by the first direction or the second direction and
wherein an architecture of the plurality of plies of the CMC insert is symmetric about a mid-plane of the turbomachine member, the mid-plane being parallel to the first plane and the mid-plane being between two plies with a substantially identical orientation.

16. The method according to claim 15 , further comprising disposing a plurality of new CMC material layers on the pl

Assignees

• Gen Electric

Inventors

• Decesare Douglas Glenn
• Dunn Daniel Gene

Classifications

• F01D25/005 Primary

  Selecting particular materials · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/12

  inducing a vortex · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title