CERAMIC MATRIX COMPOSITE STRUCTURE

• US 20100062210A1
• Filed: 09/11/2008
• Published: 03/11/2010
• Est. Priority Date: 09/11/2008
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Marini, Bonnie D.
• Granted Patent: US 8,322,983 B2
• Time in Patent Office: Days
• US Class Current: 428/99
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means
• CPC Class Codes: Y10T 428/24008 including fastener for attaching to external surface

Abstract

A composite structure (10), which may be a 2-dimensional ceramic matrix composite material, may include a first body (30) made of a composite material defining a first in-plane direction, a second body (20) made of a composite material defining a second in-plane direction wherein the first body (30) is connected with the second body (20) so that the first in-plane direction is substantially normal to the second in-plane direction. The second body (20) of the composite structure may include a first leg (24), a first bolting surface (22) extending from the first leg (24) and at least one aperture (56) formed in the first bolting surface (22) substantially normal to the second in-plane direction. A first recess (32) may be formed within the first body (30) sized to receive the first leg (24).

Claims

1. ) A composite structure comprising:

a first body made of a composite material defining a first in-plane direction;

a second body made of a composite material defining a second in-plane direction; and

the first body connected with the second body so that the first in-plane direction is substantially normal to the second in-plane direction.

2. ) The composite structure of claim 1, the second body comprising:

a first leg;

a first bolting surface extending from the first leg; and

at least one aperture formed in the first bolting surface substantially normal to the second in-plane direction.

3. ) The composite structure of claim 2 further comprising:

a first recess formed within the first body sized to receive the first leg; and

a filament wound over a portion of the first recess to retain the first leg within the first recess.

4. ) The composite structure of claim 3 further comprising:

a slot formed within the first leg; and

a key fitted within the slot and affixed to the first body.

5. ) The composite structure of claim 1 further comprising the first body and the second body fabricated from a 2-dimensional ceramic matrix composite material and forming a component within a combustion turbine.

6. ) The composite structure of claim 5 further comprising:

a first recess formed within the first body sized to received a portion of the second body so that the second body may move relative to the first body; and

a filament wound over a portion of the first recess to retain the portion of the second body within the first recess.

7. ) The composite structure of claim 1 further comprising:

the first body fabricated from a 2-dimensional ceramic matrix composite material and forming a component within a combustion turbine;

the second body fabricated from a 2-dimensional ceramic matrix composite material forming a bolt flange, the bolt flange comprising a first leg connected with the first body and a bolting surface extending from the first leg; and

at least one aperture formed within the bolting surface in a direction substantially normal to the second in-plane direction.

8. ) The composite structure of claim 7 further comprising a thermal barrier coating deposited on a surface of the first body.

9. ) An assembly for installation in a gas turbine engine, the assembly comprising:

a component fabricated from a ceramic matrix composite material forming a first fiber direction; and

a bolt flange fabricated from a ceramic matrix composite material forming a second fiber direction, the bolt flange comprising a leg affixed to the component and a bolting surface extending from the leg wherein the first fiber direction is substantially normal to the second fiber direction.

10. ) The assembly of claim 9 further comprising at least one aperture formed through the bolting surface and substantially normal to the second fiber direction.

11. ) The assembly of claim 10 further comprising an upper surface of the leg of the bolt flange positioned beneath an exterior surface of the component.

12. ) The assembly of claim 9 further comprising a recess formed within the component wherein the leg of the bolt flange is affixed within the recess.

13. ) The assembly of claim 12 further comprising a filament wound onto the component and over the leg.

14. ) The assembly of claim 12 further comprising:

a slot formed within the bolt flange; and

a key fitted within the slot and affixed to the component.

15. ) A component for use within a combustion turbine, the component comprising:

a composite material forming the component;

a plurality of bolt flanges affixed to the component, each of the plurality of bolt flanges fabricated from a composite material defining a first fiber direction; and

means for fastening the component to another structure within the combustion turbine.

16. ) The component of claim 15 further comprising at least two of the plurality of bolt flanges laterally offset along a longitudinal axis of the component.

17. ) The component of claim 15 further comprising the means for fastening comprising at least one aperture formed within each of the plurality of bolt flanges, the at least one aperture formed substantially normal to the first fiber direction.

18. ) The component of claim 17 further comprising at least one recess formed within the composite material forming the component wherein at least one of the plurality of bolt flanges is affixed to the component within the recess.

19. ) The component of claim 15 further comprising:

the means for fastening comprising at least one aperture formed within each of the plurality of bolt flanges, the at least one aperture formed substantially normal to the first fiber direction;

a plurality of recesses formed within the composite material forming the component wherein a respective one of the plurality of bolt flanges is affixed to the component within a respective one of the plurality of recesses; and

a filament wound over the plurality of recesses to retain the plurality of bolt flanges within the plurality of recesses.

20. ) The component of claim 15 further comprising:

each of the plurality of bolt flanges comprising a leg and a bolting surface, the bolting surface extending substantially normal from the leg;

a plurality of recesses formed within the composite material forming the component wherein a respective leg of the plurality of bolt flanges is affixed to the component within a respective one of the plurality of recesses;

a filament wound over the plurality of recesses and the respective legs to retain the plurality of bolt flanges within the plurality of recesses; and

the means for fastening comprising at least one aperture formed within each of the respective bolting surfaces of the plurality of bolt flanges, the at least one aperture formed substantially normal to the first fiber direction.