Turbine shroud with mounted full hoop blade track

Patent metadata

Field	Value
Publication number	US-10247040-B2
Application number	US-201615000655-A
Country	US
Kind code	B2
Filing date	Jan 19, 2016
Priority date	Jan 19, 2016
Publication date	Apr 2, 2019
Grant date	Apr 2, 2019

Abstract

A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.

First claim

What is claimed is:

1. A gas turbine engine comprising
a turbine case arranged around a central axis of the gas turbine engine and formed to include a plurality of outer keyways extending in a radial direction through the turbine case,
a turbine shroud axially aligned with the turbine case and including (i) an annular carrier arranged around the central axis of the gas turbine engine and formed to include a plurality of outer pin receivers and a plurality of inner keyways, wherein the annular carrier includes a plurality of bosses that extend radially outward away from an outer radial carrier surface of the annular carrier and each boss is formed to include one of the outer pin receivers, and (ii) a one-piece annular runner formed to include a plurality of inner pin receivers extending in a radial direction from an outer radial runner surface toward an inner radial runner surface of the one-piece annular runner,
a plurality of outer insert pins, each outer insert pin arranged to extend through one of the outer keyways formed in the turbine case into a corresponding one of the plurality of outer pin receivers formed in the annular carrier to locate the turbine case and the annular carrier relative to the central axis while allowing radial growth of the turbine case and the annular carrier at different rates during use of the gas turbine engine, and
a plurality of inner insert pins, each inner insert pin arranged to extend through one of the inner keyways formed in the annular carrier into a corresponding one of the plurality of inner pin receivers formed in the one-piece annular runner to locate the annular carrier and the one-piece annular runner relative to the central axis while allowing radial growth of the annular carrier and the one-piece annular runner at different rates during use of the gas turbine engine.

2. The gas turbine engine of claim 1 , wherein the annular carrier is formed to define a radially inwardly-opening carrier channel that extends circumferentially around the central axis, the plurality of outer pin receivers extend radially through the annular carrier and open into the radially inwardly-opening carrier channel, and at least one of the outer insert pins is a hollow outer insert pin formed to include a cooling passage extending through the hollow outer insert pin and arranged to direct pressurized air through the cooling passage through the turbine case and the annular carrier into the carrier channel.

3. The gas turbine engine of claim 2 , wherein the turbine case includes a plurality of turbine case bosses that extend radially outward away from the turbine case and each boss is formed to include one of the outer keyways.

4. The gas turbine engine of claim 1 , wherein the outer keyways, the outer pin receivers, the inner keyways, the inner pin receivers, the outer insert pins, and the inner insert pins are unthreaded.

5. The gas turbine engine of claim 4 , wherein the annular carrier 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 outer pin receivers are formed in the midsection of the annular carrier.

6. The gas turbine engine of claim 4 , wherein the one-piece 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 inner pin receivers are formed in the midsection of the one-piece annular runner.

7. The gas turbine engine of claim 1 , wherein the outer pin receivers included in the annular carrier are spaced apart from each other circumferentially around the annular carrier, the inner pin receivers included in the one-piece annular runner are spaced apart from each other circumferentially around the one-piece annular runner, and the inner pin receivers are circumferentially offset from the outer pin receivers.

8. The gas turbine engine of claim 1 , wherein the annular carrier includes at least three outer insert pins and at least three corresponding outer pin receivers and the one-piece annular runner includes at least three inner insert pins and at least three corresponding inner pin receivers.

9. The gas turbine engine of claim 8 , wherein the outer pin receivers extend in a radial direction through the annular carrier from an outer radial carrier surface to an inner radial carrier surface included in the annular carrier.

10. A gas turbine engine comprising
a turbine case formed to include an outer keyway extending through the turbine case,
a turbine shroud including (i) a carrier formed to include an inner keyway extending through the carrier and an outer pin receiver, wherein the carrier includes a plurality of bosses that extend radially outward away from an outer radial carrier surface of the carrier and each boss is formed to include one of the outer pin receivers, and (ii) an annular runner formed to include an inner pin receiver,
an outer insert pin extending through the outer keyway into the outer pin receiver to block rotation of the carrier relative to the turbine case, and
an inner insert pin extending through the inner keyway formed in the carrier into the inner pin receiver formed in the annular runner to block rotation of the annular runner relative to the carrier.

11. The gas turbine engine of claim 10 , wherein the carrier is formed to define a radially inwardly-opening carrier channel that extends around a central axis of the gas turbine engine, the outer pin receiver extends radially through the carrier and opens into the radially inwardly-opening carrier channel, and the outer insert pin is a hollow outer insert pin formed to include a cooling passage extending through the hollow outer insert pin and arranged to direct pressurized air through the cooling passage through the turbine case and the carrier into the carrier channel.

12. The gas turbine engine of claim 10 , wherein the turbine case includes a turbine case boss that extends radially outward away from the turbine case and the turbine case boss is formed to include the outer keyway.

13. The gas turbine engine of claim 10 , wherein the outer keyway, the outer pin receiver, the inner keyway, the inner pin receiver, the outer insert pin, and the inner insert pin are unthreaded.

14. The gas turbine engine of claim 13 , wherein the outer pin receiver extends in a radial direction partway through the carrier from an outer radial carrier surface toward an inner radial carrier surface of the carrier.

15. The gas turbine engine of claim 10 , wherein the carrier 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 outer pin receiver is formed in the midsection of the carrier.

16. A gas turbine engine comprising
a turbine case arranged around a central axis of the gas turbine engine and formed to include a plurality of outer keyways extending in a radial direction through the turbine case,
a turbine shroud axially aligned with the turbine case and including (i) an annular carrier arranged around the central axis of the gas turbine engine and formed to include a plurality of outer pin receivers and a plurality of inner keyways, and (ii) a one-piece annular runner formed to include a plurality of inner pin receivers extending in a radial direction from an outer radial runner surface toward an inner radial runner surface of the one-piece annular runner,
a plurality of outer insert pins, each outer insert pin arranged to extend through one of the

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Varney Bruce E
• Petty Jack D
• Vetters Daniel K
• Clemens Eugene

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F05D2250/232

  conical · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title