Full hoop blade track with axially keyed features

Patent metadata

Field	Value
Publication number	US-10370985-B2
Application number	US-201514972568-A
Country	US
Kind code	B2
Filing date	Dec 17, 2015
Priority date	Dec 23, 2014
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

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 locates the ceramic blade track relative to the metallic carrier.

First claim

What is claimed is:

1. A turbine shroud for use in a gas turbine engine having a central axis, the turbine shroud comprising
an annular metallic carrier,
a one-piece annular ceramic runner concentric with the annular metallic carrier that extends around the central axis, the one-piece annular ceramic runner having a surface that faces radially outward away from the central axis, and
a cross-key connection formed between the annular metallic carrier and the one-piece annular ceramic blade track to locate the one-piece annular ceramic runner relative to the annular metallic carrier, the cross-key connection including a plurality of keys and a plurality of corresponding keyways that receive the plurality of keys,
wherein the plurality of keys extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis without extending radially outward from the surface and the plurality of corresponding keyways that are formed in the annular metallic carrier.

2. The turbine shroud of claim 1 , wherein the one-piece ceramic runner comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material.

3. The turbine shroud of claim 2 , wherein the ceramic matrix material includes silicon-carbide and the ceramic-containing reinforcements include silicon-carbide.

4. The turbine shroud of claim 2 , wherein the ceramic-containing reinforcements include plies of reinforcing fabric that extends around the central axis.

5. The turbine shroud of claim 2 , wherein the plurality of keys are integral with the one-piece annular ceramic runner and each of the plurality of keys comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material.

6. The turbine shroud of claim 1 , wherein the plurality of keys extend from an aft side of the one-piece annular ceramic runner into the plurality of corresponding keyways.

7. The turbine shroud of claim 6 , wherein the plurality of keys and the one-piece annular ceramic runner have about the same thickness when viewed from a forward side of the runner.

8. A turbine shroud for use in a gas turbine engine having a central axis, the turbine shroud comprising
an annular metallic carrier,
a one-piece annular ceramic runner concentric with the annular metallic carrier that extends around the central axis,
a cross-key connection formed between the annular metallic carrier and the one-piece annular ceramic blade track to locate the one-piece annular ceramic runner relative to the annular metallic carrier, the cross-key connection including a plurality of keys and a plurality of corresponding keyways that receive the plurality of keys, and
a plurality of insulator tabs that extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis circumferentially between the plurality of keys and radially inward of a portion of the annular metallic carrier so that the plurality of insulator tabs insulate at least some of the annular metallic carrier from hot gasses during use of the turbine shroud within a gas turbine engine,
wherein the plurality of keys extend in the axial direction from the one-piece annular ceramic runner parallel to the central axis and the plurality of corresponding keyways that are formed in the annular metallic carrier.

9. The turbine shroud of claim 8 , wherein the plurality of insulator tabs are integral with the one-piece annular ceramic runner and each of the plurality of insulator tabs comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material.

10. The turbine shroud of claim 8 , wherein the plurality of keys and the one-piece annular ceramic runner have about the same thickness when viewed from a forward side of the runner and the plurality of insulator tabs are thinner than the one-piece annular ceramic runner when viewed from a forward side of the runner.

11. The turbine shroud of claim 8 , wherein the plurality of keys extend from an aft side of the one-piece annular ceramic runner into the plurality of corresponding keyways and the plurality of insulator tabs also extend from the aft side of the one-piece annular ceramic runner circumferentially between the plurality of keyways without being received in the plurality of keyways.

12. A blade track for a gas turbine engine, the blade track comprising
a one-piece annular ceramic runner that extends around a central axis and that comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material, the one-piece annular ceramic runner having a surface that faces radially outward away from the central axis, and
a plurality of keys that extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis without extending radially outward from the surface.

13. The blade track of claim 12 , wherein the ceramic matrix material includes silicon-carbide and the ceramic-containing reinforcements include silicon-carbide.

14. The blade track of claim 12 , wherein the ceramic-containing reinforcements include plies of reinforcing fabric that extends around the central axis.

15. The blade track of claim 14 , wherein the plurality of keys are integral with the one-piece annular ceramic runner and each of the plurality of keys comprises ceramic matrix material and woven plies of ceramic-containing reinforcements suspended in the ceramic matrix material.

16. The blade track of claim 15 , wherein the plurality of keys and the one-piece annular ceramic runner have about the same thickness when viewed from a forward side of the runner.

17. A blade track for a gas turbine engine, the blade track comprising
a one-piece annular ceramic runner that extends around a central axis and that comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material,
a plurality of keys that extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis, and
a plurality of insulator tabs that extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis circumferentially between the plurality of keys.

18. The blade track of claim 17 , wherein the plurality of insulator tabs are integral with the one-piece annular ceramic runner and each of the plurality of insulator tabs comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material.

19. The blade track of claim 17 , wherein the plurality of keys and the one-piece annular ceramic runner have about the same thickness when viewed from a forward side of the runner and the plurality of insulator tabs are thinner than the one-piece annular ceramic runner when viewed from a forward side of the one-piece annular runner.

20. A method of locating a ceramic blade track having a surface that faces radially outward away from a central axis relative to a metallic carrier, the method comprising
rotating the ceramic blade track to a predetermined orientation relative to the metallic carrier,
nesting the ceramic blade track in a space formed by the metallic carrier so that the ceramic blade track is concentric with the metallic carrier, and
inserting a plurality of keys extending in an axial direction from the ceramic blade track without extending radially outward from the surface into a corresponding plurality of keyways formed in the metallic carrier to thereby establish a cross-key

Assignees

• Rolls Royce Corp

Inventors

• Walston Jeffrey A
• Sippel Aaron D
• Weaver John A
• Thomas David J

Classifications

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D5/3023 Primary

  of radial insertion type, e.g. in individual recesses · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title