Ceramic matrix composite gas turbine vane

• US 6,709,230 B2
• Filed: 05/31/2002
• Issued: 03/23/2004
• Est. Priority Date: 05/31/2002
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Morrison, Jay A., Campbell, Chris, Thompson, Daniel George, Merrill, Gary Brian, Lane, Jay Edgar, Albrecht, Harry A., Shteyman, Yevgeniy P.
• Primary Examiner(s): Nguyen, Ninh H.
• Application Number:
  US10/158,946
• Publication Number:
  US 20030223861A1
• Time in Patent Office: 662 Days
• Field of Search: 415/115, 415/200, 416/97.R, 416/97.A, 416/229.R, 416/229.A, 416/224, 416/241.B
• US Class Current: 415/115
• CPC Class Codes: C04B 2237/343 Alumina or aluminates
• CPC Class Codes: C04B 2237/38 Fiber or whisker reinforced
• CPC Class Codes: C04B 2237/62 Forming laminates or joined articles comprising holes, channels or other types of openings
• CPC Class Codes: C04B 2237/84 Joining of a first substrate with a second substrate at least partially inside the first substrate, where the bonding area is at the inside of the first substrate, e.g. one tube inside another tube
• CPC Class Codes: C04B 37/001 directly with other burned ceramic articles
• CPC Class Codes: C04B 37/008 by means of an interlayer consisting of an organic adhesive, e.g. phenol resin or pitch
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• 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: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05D 2300/50212 dissimilar
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 428/252 Glass or ceramic [i.e., fired or glazed clay, cement, etc.] [porcelain, quartz, etc.]
• CPC Class Codes: Y10T 428/257 Iron oxide or aluminum oxide

Abstract

A hybrid vane (50) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member (52) bonded to a substantially solid core member (54). The airfoil member and core member are cooled by a cooling fluid (58) passing through cooling passages (56) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond ((70) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation (72) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.

Claims

1. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

a core member disposed in the core region and joined to the ceramic matrix composite member by a bond including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein a coefficient of thermal expansion of the core member is at least 10% greater than a coefficient of thermal expansion of the ceramic matrix composite member.

2. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

core member disposed in the core region and joined to the ceramic matrix composite member by a bond including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein a coefficient of thermal expansion of the core member is in the range of >

0 to 14% greater than a coefficient of thermal expansion of the ceramic matrix composite member.

3. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

a core member disposed in the core region and joined to the ceramic matrix composite member by a bond including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein the core member has a mechanical strength that is less than a

mechanical strength of the bond.

4. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

a core member disposed in the core region and joined to the ceramic matrix composite member by a bond including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein a ratio of an elastic modulus of the core member to an elastic modulus of the ceramic matrix composite member is less than one half.

5. The turbine component of claim 4, wherein a ratio of an elastic modulus of the core member to an elastic modulus of the ceramic matrix composite member is less than one third.

6. The turbine component of claim 4, wherein a ratio of an elastic modulus of the core member to an elastic modulus of the ceramic matrix composite member is less than one tenth.

7. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

a core member disposed in the core region and joined to the ceramic matrix composite member by a band including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein the cooling channel comprises a groove formed in an outer

surface of the core member.

8. The turbine component of claim 7, further comprising a layer of an insulating material disposed over the outside surface of the ceramic matrix composite member.

9. The turbine component of claim 8, where an outside surface of the insulating material comprises an airfoil shape.

10. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

a corn member disposed in the core region and joined to the ceramic matrix composite member by a bond including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein the cooling channel comprises;

an inlet plenum formed along a length of the core member;

a first plurality of grooves formed proximate an outside surface of the core member; and

an opening between the inlet plenum and each of the first plurality of grooves.

11. The turbine component of claim 10, further comprising:

each of the first plurality of grooves terminating in an outlet plenum formed along the length of the core member; and

a second plurality of grooves having respective inlets connected to the outlet plenum and extending proximate a trailing edge of the turbine vane.

12. A turbine component comprising:

a ceramic matrix composite member having an inside surface defining a core region;

a core member disposed in the core region and joined to the ceramic matrix composite member by a bond including at least 30% of the inside surface of the ceramic matrix composite member; and

a cooling channel formed in the core member for the passage of a cooling fluid;

wherein a first section of the core member comprises a material different than a second section of the core member.

13. The turbine component of claim 12, wherein the second section comprises a trailing edge section spaced apart from the first section to define a plenum.

14. The turbine component of claim 13, further comprising a first number of cooling channels formed in the first section and a second number of cooling channels different than the first number formed in the section.

15. A turbine component comprising:

a ceramic matrix composite member having an inner surface defining a core region;

a core member disposed in the core region and bonded to the ceramic matrix composite member inner surface;

a cooling channel formed in the core member for the passage of a cooling fluid for removing heat from the core member, the bond between the core member and the ceramic matrix composite member providing a conductive heat removal pathway between the ceramic matrix composite member and the core member;

wherein the core member is formed of a material having a mechanical strength that is less than a mechanical strength of the bond in order to safeguard the integrity of the heat removal pathway.

16. The turbine component of claim 15, wherein the core member is bonded to the ceramic matrix composite member by a bond including at least 30% of the inner surface of the ceramic matrix composite member.

17. The turbine component of claim 15, wherein the core member is bonded to the ceramic matrix composite member by a bond including at least 50% of the inner surface of the ceramic matrix composite member.

18. The turbine component of claim 15, wherein the core member is bonded to the ceramic matrix composite member by a bond including at least 75% of the inner surface of the ceramic matrix composite member.

19. The turbine component of claim 15, wherein the core member is bonded to the ceramic matrix composite member by a bond including at least 80% of the inner surface of the ceramic matrix composite member.

20. The turbine component of claim 15, wherein a coefficient of thermal expansion of the core member is at least 10% greater than a coefficient of thermal expansion of the ceramic matrix composite member.

21. The turbine component of claim 15, wherein a coefficient of thermal expansion of the core member is in the range of >

0 to 14% greater than a coefficient of thermal expansion of the ceramic matrix composite member.

22. The turbine component of claim 15, wherein a ratio of an elastic modulus of the core member to an elastic modulus of the ceramic matrix composite member is less than one half.

23. The turbine component of claim 15, wherein a ratio of an elastic modulus of the core member to an elastic modulus of the ceramic matrix composite member is less than one third.

24. The turbine component of claim 15, wherein a ratio of an elastic modulus of the core member to an elastic modulus of the ceramic matrix composite member is less than one tenth.

25. The turbine component of claim 15, further comprising a layer of an insulating material disposed over the outside surface of the ceramic matrix composite member.

26. The turbine component of claim 25, where an outside surface of the insulating material comprises an airfoil shape.

27. The turbine component of claim 15, wherein the core member comprises a plurality of sections.

28. The turbine component of claim 27, wherein a first section of the core member comprises a material different than a second section of the core member.

29. The turbine component of claim 28, wherein the second section comprises a trailing edge section spaced apart from the first section to define a plenum.

30. The turbine component of claim 29, further comprising a first number of cooling channels formed in the first section and a second number of cooling channels different than the first number formed in the section.

31. The turbine component of claim 15, wherein the cooling channel comprises a groove formed in an outer surface of the core member.

32. The turbine component of claim 15, wherein the cooling channel comprises a passage formed through the core member.

33. A turbine component comprising:

a ceramic matrix composite member having an inner surface defining a core region;

a core member disposed in the core region and bonded to the ceramic matrix composite member inner surface;

wherein a coefficient of thermal expansion of the core member is greater than a coefficient of thermal expansion of the ceramic matrix composite member.

34. A turbine component comprising:

a ceramic matrix composite member having an inner surface defining a core region;

a core member disposed in the core region and bonded to the ceramic matrix composite member inner surface by a bond, the bond providing a conductive heat removal pathway between the ceramic matrix composite member and the core member;

wherein the core member is formed of a material having a mechanical strength that is less than a mechanical strength of the bond in order to safeguard the integrity of the heat removal pathway.

35. A tribute component comprising:

a ceramic matrix composite member having an inner surface defining a core region;

a core member disposed in the core region and bonded to the ceramic matrix composite member inner surface;

wherein a ratio of an elastic modulus of the core member to an elastic modulus at the ceramic matrix composite member is less than one half.

36. A turbine component comprising:

a ceramic matrix composite member having an inner surface defining a core region;

a core member having groove formed in an outer surface, the core member disposed in the core region and bonded to the ceramic matrix composite member inner surface with the groove defining a cooling passage for directing a cooling fluid between the core member and the ceramic matrix composite member.