CERAMIC MATRIX COMPOSITE VANE WITH CHORDWISE STIFFENER

• US 20080181766A1
• Filed: 01/18/2005
• Published: 07/31/2008
• Est. Priority Date: 01/18/2005
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Morrison, Jay A., Campbell, Christian X., Shteyman, Yevgeniy, Albrecht, Harry A.
• Granted Patent: US 7,435,058 B2
• Time in Patent Office: Days
• US Class Current: 415/116
• CPC Class Codes: F01D 5/14 Form or construction selecting particular materials, measures against erosion or corrosion F01D5/28
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: F05D 2300/21 Oxide ceramics
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced

Abstract

A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.

Claims

1. (canceled)

4-6. -6. (canceled)

7. A turbine component comprising:

a ceramic matrix composite defining a wall;

a stiffener disposed on said wall, said stiffener generally extending along a chord length of the component, wherein the stiffener is disposed on an outer surface of said wall; and

a layer of insulation material joined to said stiffener.

2. The turbine component of claim 7 wherein said component is internally pressurized.

3. The turbine component of claim 7 wherein the wall defines a hollow interior for the turbine component.

8. The turbine component of claim 7 wherein said stiffener constitutes an integral structure relative to said wall.

9. The turbine component of claim 7 wherein said stiffener constitutes a separate structure relative to said wall.

11. The turbine component of claim 7 wherein said stiffener defines a cavity, said cavity filled with a fluid.

13. The turbine component of claim 7 wherein said stiffener comprises at least one rib along a periphery of the wall.

17. The turbine component of claim 7 wherein said stiffener comprises an angle relative to the chord-length, said angle based on a type of pressure load for the turbine component, said type of pressure load selected from the group consisting of an internal pressure load and an external pressure load.

10. A turbine component comprising:

a ceramic matrix composite defining a wall; and

a stiffener disposed on said wall, said stiffener generally extending along a chord length of the component, wherein said stiffener defines a cavity, said cavity filled with a ceramic material.

12. A turbine component comprising:

a ceramic matrix composite defining a wall; and

a stiffener disposed on said wall, said stiffener generally extending along a chord length of the component, wherein said stiffener comprises a stack of fiber material deposited on said wall.

14. A turbine component comprising:

a ceramic matrix composite defining a wall;

a stiffener disposed on said wall, said stiffener generally extending along a chord length of the component, wherein said stiffener is disposed over a predefined region of the component that comprises less than an entire chord length of the component, wherein at least a section of the stiffener is disposed on an outer surface of said wall; and

a layer of insulation material joined to said section of the stiffener.

15. The turbine component of claim 14 wherein said predefined region is selected from the group consisting of a leading edge region and trailing edge region of the component.

16. A turbine component comprising:

a ceramic matrix composite defining a wall; and

a stiffener disposed on said wall, said stiffener generally extending along a chord length of the component, wherein the stiffener comprises a first stiffener section disposed on an inner surface of said wall and a second stiffener section disposed on an outer surface of said wall.

18. A turbine component comprising:

a ceramic matrix composite defining a wall;

a stiffener disposed on an outer surface of said wall, said stiffener generally extending along a chord length of the component, wherein said stiffener comprises a first stiffener configuration over a predefined first region of the component, and further comprises a second stiffener configuration over a predefined second region of the component, the second and first stiffener configurations being different relative to one another; and

a layer of insulation material joined to said stiffener at least over one of said first and second regions of the component.

19-21. -21. (canceled)

23. A turbine vane comprising:

a ceramic matrix composite wall member comprising an inner surface defining a core region, and an outer surface defining an airfoil shape having a chord;

a stiffener attached to the wall member and generally extending in a chord-wise direction over at least a portion of a length of the chord, wherein the stiffener is disposed on said outer surface of said wall member; and

a layer of insulation material joined to said stiffener.

22. The turbine vane of claim 23 further comprising a core member in said core region and joined to said stiffener.

24. The turbine vane of claim 23 wherein said stiffener constitutes an integral structure relative to said wall member.

25. The turbine vane of claim 23 wherein said stiffener constitutes a separate structure relative to said wall member.