Turbine component connection with thermally stress-free fastener

• US 9,845,692 B2
• Filed: 05/05/2015
• Issued: 12/19/2017
• Est. Priority Date: 05/05/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Jamison, Joshua Brian
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US14/704,406
• Publication Number:
  US 20160326896A1
• Time in Patent Office: 959 Days
• CPC Class Codes: F01D 25/005 Selecting particular materials
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/642 using maintaining alignment while permitting differential dilatation
• CPC Class Codes: F05D 2240/128 Nozzles
• CPC Class Codes: F05D 2250/42 with two degrees of freedom
• CPC Class Codes: F05D 2250/711 convex
• CPC Class Codes: F05D 2260/36 by a form fit connection, e.g. by interlocking
• CPC Class Codes: F05D 2300/17 Alloys
• 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

Abstract

A turbine component assembly for a gas turbine engine includes: a first component having a first coefficient of thermal expansion and including an end face; a second component including a mating surface abutting the end face; and a fastener having a second coefficient of thermal expansion different from the first coefficient of thermal expansion, the fastener including a shank engaging the second component and an enlarged head engaging a mounting slot in the first component; wherein the mating surface and the end face shaped to permit relative pivoting movement between the first and second components.

Claims

1. A turbine component assembly for a gas turbine engine, comprising:

a first component having a first coefficient of thermal expansion and including an end face;

a second component including a mating surface abutting the end face; and

a fastener having a second coefficient of thermal expansion different from the first coefficient of thermal expansion, the fastener including a shank engaging the second component and an enlarged head engaging a mounting slot in the first component;

wherein the mating surface and the end face shaped to permit relative pivoting movement between the first and second components.

2. The assembly of claim 1 wherein the mating surface has a mounting hole passing therethrough which receives the shank of the fastener.

3. The assembly of claim 1 wherein the mating surface and the end face are shaped to permit relative pivoting movement therebetween, about two mutually perpendicular axes.

4. The assembly of claim 1 wherein the mating surface is convex-outward-curved and the end face is planar.

5. The assembly of claim 1 wherein the shank is connected to a retainer that bears against the second component.

6. The assembly of claim 5 wherein the retainer comprises a washer metallurgically bonded to the shank.

7. The assembly of claim 1 wherein the head of the fastener includes a proximate portion adjacent the shank and a distal portion, the proximate portion having a surface with a diverging shape.

8. The assembly of claim 7 wherein the proximate portion is a body of revolution.

9. The assembly of claim 1 wherein the mounting slot has a cross-sectional shape comprising an entrance, an enlarged end chamber, and a tapered section interconnecting the entrance and the end chamber, the tapered section comprising a pair of spaced-apart walls which diverge from each other.

10. The assembly of claim 1 wherein the fastener comprises a metallic alloy.

11. The assembly of claim 1 wherein the first component comprises a ceramic matrix composite.

12. A turbine nozzle apparatus for a gas turbine engine, comprising:

an annular inner band;

an annular outer band circumscribing the inner band;

a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and

a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, wherein one of the tip end and the root end is connected to the respective band by a fastener having a shank engaging the band and an enlarged head engaging a mounting slot in the non-structural vane.

13. The apparatus of claim 12 wherein one of the inner and outer bands includes a plurality of blind pockets, each blind pocket receiving one of the ends of the non-structural vanes, each blind pocket including a floor with a mounting hole passing therethrough which receives the shank of the fastener.

14. The apparatus of claim 13 wherein the floor and an end face of the non-structural vane are shaped to permit relative pivoting movement therebetween.

15. The apparatus of claim 14 wherein the floor and the end face are shaped to permit relative pivoting movement therebetween, about two mutually perpendicular axes.

16. The apparatus of claim 12 herein the floor is convex-outward-curved and the end face is planar.

17. The apparatus of claim 13 wherein the shank is connected to a retainer that bears against the floor of the blind pocket.

18. The apparatus of claim 17 wherein the retainer comprises a washer welded to the shank.

19. The apparatus of claim 12 wherein the head of the fastener includes a proximate portion adjacent the shank and a distal portion, the proximate portion having a surface with a diverging shape.

20. The apparatus of claim 19 wherein the proximate portion is a body of revolution.

21. The apparatus of claim 12 wherein the mounting slot has a cross-sectional shape comprising an entrance, an enlarged end chamber, and a tapered section interconnecting the entrance and the end chamber, the tapered section comprising a pair of spaced-apart walls which diverge from each other.

22. The apparatus of claim 12 wherein the fastener comprises a metallic alloy.

23. The apparatus of claim 12 wherein one of the inner and outer bands includes:

a plurality of spaced-apart apertures formed therein; and

a cover received in each aperture, the cover including at least one blind pocket, each blind pocket receiving one of the ends of the non-structural vanes.

24. The apparatus of claim 12 wherein the non-structural vanes comprise a ceramic matrix composite.

25. The apparatus of claim 12 wherein the structural vanes comprise a metallic alloy.

26. The apparatus of claim 12 wherein:

the inner band includes a plurality of blind pockets, each blind pocket receiving one of the ends of the non-structural vanes, each blind pocket including a floor with a mounting hole passing therethrough which receives the shank of the fastener; and

the outer band includes;

a plurality of spaced-apart apertures formed therein; and

a cover received in each aperture, the aperture including a plurality of blind pockets, each blind pocket receiving one of the tip ends of one of the non-structural vanes.