Turbine shroud with tubular runner-locating inserts

Patent metadata

Field	Value
Publication number	US-2016208635-A1
Application number	US-201614989263-A
Country	US
Kind code	A1
Filing date	Jan 6, 2016
Priority date	Jan 15, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend through the carrier to couple the annular runner with the carrier.

First claim

What is claimed is:

1 . A turbine shroud comprising
an annular metallic carrier arranged around a central axis of the turbine shroud and formed to include a plurality of keyways extending in a radial direction into the annular metallic carrier, and a blade track including a ceramic annular runner and a plurality of ceramic inserts extending outward in a radial direction away from the ceramic annular runner, wherein each of the plurality of ceramic inserts are tubular and are arranged to extend into a corresponding one of the plurality of keyways formed in the annular metallic carrier to locate the blade track and the annular metallic carrier relative to the central axis while allowing radial growth of the annular metallic carrier and the blade track at different rates during use of the turbine shroud.

2 . The turbine shroud of claim 1 , wherein the ceramic annular runner includes a forward section, an aft section spaced apart axially from the forward section, and a midsection extending between the forward section and the aft section and the ceramic inserts extend outwardly from the midsection of the ceramic annular runner.

3 . The turbine shroud of claim 1 , wherein the blade track is formed to include a sensor passage extending radially through at least one of the ceramic inserts and the ceramic annular runner.

4 . The turbine shroud of claim 3 , further comprising a sensor coupled to the at least one ceramic insert for movement therewith and the sensor extends radially inward through the sensor passage toward the ceramic annular runner.

5 . The turbine shroud of claim 4 , wherein the sensor comprises a blade-tip probe.

6 . The turbine shroud of claim 1 , wherein the annular metallic carrier includes a forward side and an aft side spaced apart axially from the forward side and each keyway opens into the aft side and extends axially toward the forward side.

7 . The turbine shroud of claim 1 , wherein each insert is formed to include an insert aperture extending radially through the insert.

8 . The turbine shroud of claim 1 , wherein each insert has a round shape when viewed radially inwardly from radially outward of the blade track.

9 . A blade track comprising
a ceramic annular runner including an outer radial surface and an inner radial surface spaced apart radially from the outer radial surface, and a plurality of ceramic inserts coupled with the ceramic annular runner for movement therewith and extending radially outward away from the outer radial surface, wherein each insert is tubular and forms an insert aperture that extends radially through the insert.

10 . The blade track of claim 9 , wherein the ceramic annular runner includes a forward section, an aft section spaced apart axially from the forward section, and a midsection extending between the forward section and the aft section and the ceramic inserts are located in the midsection of the ceramic annular runner.

11 . The blade track of claim 9 , wherein the ceramic annular runner is formed to include a plurality of insert receivers and a portion of each ceramic insert is positioned in a corresponding insert receiver.

12 . The blade track of claim 11 , wherein the insert receivers extend in a radial direction partway through the ceramic annular runner from the outer radial surface toward the inner radial surface.

13 . The blade track of claim 9 , wherein each ceramic insert has a round shape when viewed from radially outward of the blade track.

14 . The blade track of claim 13 , wherein at least one ceramic insert includes an insert aperture extending therethrough, the ceramic annular runner further includes a runner aperture extending in a radial direction through the ceramic annular runner, and the runner aperture is aligned with the insert aperture to define a sensor passage that extends radially through the blade track.

15 . The blade track of claim 14 , further comprising a sensor coupled to a ceramic insert for movement therewith and the sensor extends radially through the sensor passage.

16 . The blade track of claim 15 , wherein the sensor comprises a blade-tip probe.

17 . The blade track of claim 9 , wherein the ceramic annular runner and the inserts consist essentially of ceramic matrix composite material.

18 . The blade track of claim 9 , wherein the ceramic annular runner and the inserts consist essentially of silicon carbide containing matrix and silicon carbide containing reinforcements.

19 . A method of assembling a turbine shroud comprising
providing a blade track including an annular runner and a plurality of tubular inserts coupled with the annular runner and extending radially outward away from the annular runner, rotating the annular runner to a predetermined orientation relative to a carrier so that keyways formed in the carrier are aligned with corresponding tubular inserts, and nesting the annular runner into the carrier so that the tubular inserts are received in the keyways to thereby establish a connection between the blade track and the carrier.

20 . The method of claim 19 , further comprising inserting a sensor through an insert aperture that extends radially through a tubular insert and into a runner aperture that extends radially through the annular runner.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Vetters Daniel K
• Shi Jun
• Walston Jeffrey A
• Sippel Aaron D

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D11/08 Primary

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

• F05D2300/2261

  of silicon · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title