Full hoop blade track with axially keyed features

Patent metadata

Field	Value
Publication number	US-2016177753-A1
Application number	US-201514972568-A
Country	US
Kind code	A1
Filing date	Dec 17, 2015
Priority date	Dec 23, 2014
Publication date	Jun 23, 2016
Grant date	—

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, 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 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 . The turbine shroud of claim 1 , further comprising a plurality of insulator tabs 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.

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, and a plurality of keys that extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis.

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

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

15 . The turbine shroud 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 turbine shroud 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 . The turbine shroud of claim 12 , further comprising a plurality of insulator tabs 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 turbine shroud 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 turbine shroud 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 relative to a metallic retainer, the method comprising
rotating the ceramic blade track to a predetermined orientation relative to the metallic retainer, nesting the ceramic blade track in a space formed by the metallic retainer so that the ceramic blade track is concentric with the metallic retainer, and inserting a plurality of keys extending in an axial direction from the ceramic blade track into a corresponding plurality of keyways formed in the metallic carrier to thereby establish a cross-key connection between the ceramic blade track and the metallic carrier.

Assignees

• Rolls Royce Corp

Inventors

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

Classifications

• F01D5/3023 Primary

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

• F01D5/284 Primary

  Selection of ceramic materials · CPC title

• F01D11/122

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

• F01D11/08

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

• F01D9/04

  forming ring or sector · CPC title