TURBINE SHROUD

• US 20140271144A1
• Filed: 12/03/2013
• Published: 09/18/2014
• Est. Priority Date: 03/13/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Landwehr, Sean E., Westphal, William, Freeman, Ted J., Chamberlain, Adam L.
• Granted Patent: US 10,094,233 B2
• Time in Patent Office: Days
• US Class Current: 415/173.1
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2230/64 using positioning or alignment devices for aligning or centring, e.g. pins
• 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 29/49321 Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Abstract

A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and inserts included in the blade track. The inserts are bonded to an annular runner also included in the blade track by a braze layer.

Claims

1. A turbine blade track comprising

an annular ceramic runner formed to include a plurality of cutouts extending inward in a radial direction from an outer radial surface of the annular ceramic runner toward an inner radial surface of the annular ceramic runner, and

a plurality of inserts each arranged to extend into a corresponding one of the plurality of cutouts formed in the annular ceramic runner from the outer radial surface of the annular ceramic runner toward the inner radial surface of the annular ceramic runner.

2. The turbine blade track of claim 1, further comprising a plurality of braze layers arranged between the annular ceramic runner and each of the plurality of inserts.

6. The turbine blade track of claim 1, wherein each of the plurality of inserts extend outward in the radial direction from the outer radial surface of the annular ceramic runner to form keys included in the turbine blade track.

14. The turbine blade track of claim 1, wherein each of the plurality of inserts includes an aft axial surface that is coplanar with an aft axial surface of the annular ceramic runner.

15. The turbine blade track of claim 1, wherein each of the plurality of inserts is formed to include a keyway extending inward in the radial direction from an outer radial surface of each insert.

16. The turbine blade track of claim 15, wherein the keyway of each of the plurality of inserts extends aft from a forward axial surface of each insert.

18. The turbine blade track of claim 1, wherein the annular ceramic runner consists essentially of ceramic matrix composite.

21. The turbine blade track of claim 18, wherein the insert consists essentially of ceramic matrix composite.

3-5. -5. (canceled)

7-9. -9. (canceled)

11-13. -13. (canceled)

17. (canceled)

19-20. -20. (canceled)

22. A turbine shroud comprising

an annular metallic carrier,

a blade track including a ceramic annular runner formed to include a cutout, an insert arranged to extend into the cutout, and a braze layer bonded to the ceramic annular runner and the cutout.

23. The turbine shroud of claim 22, further comprising a cross-key connection formed between the annular metallic carrier and the blade track to locate the blade track relative to the annular metallic carrier, the cross-key connection including a plurality of keys and a plurality of corresponding keyways.

24. The turbine shroud of claim 23, wherein the plurality of keys extend in a radial direction from one of the annular metallic carrier and the one-piece ceramic blade track, and the plurality of corresponding keyways are formed to extend in the radial direction into the other of the annular metallic carrier and the blade track.

25. The turbine shroud of claim 24, wherein the plurality of keys are formed by the inserts included in the blade track.

26. The turbine shroud of claim 24, wherein the keyways are formed in the inserts included in the blade track.

30. The turbine shroud of claim 24, wherein the annular ceramic runner consists essentially of ceramic matrix composite.

27-29. -29. (canceled)

31-32. -32. (canceled)

33. A method of making a turbine blade track comprising the steps of

placing a plurality of inserts into corresponding cutouts formed in an annular runner, and

brazing the inserts to the annular runner to form a braze layer between each of the inserts and the annular runner.

34. The method of claim 33, wherein the braze layers comprise silicon and a transition metal.

37. The method of claim 33, wherein the annular ceramic runner consists essentially of ceramic matrix composite.

38. The method of claim 33, wherein the annular ceramic runner consists essentially of silicon carbide matrix and silicon carbide fibers.

35-36. -36. (canceled)

39. (canceled)