Turbine shroud

Patent metadata

Field	Value
Publication number	US-10371008-B2
Application number	US-201514972444-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 and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.

First claim

What is claimed is:

1. A turbine shroud comprising
an annular metallic carrier formed to include a plurality of apertures that extend in a radial direction through the annular metallic carrier,
a solid blade track formed as a continuous full hoop and including a ceramic annular runner and a plurality of pin receivers that extend inwardly in a radial direction partway into the ceramic annular runner from an outer radial surface toward an inner radial surface of the ceramic annular runner, and
a plurality of insert pins each arranged to extend through one of the plurality of apertures formed in the annular metallic carrier into a corresponding one of the plurality of pin receivers to locate the ceramic annular runner relative to the annular metallic carrier.

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 pin receivers are formed in the midsection of the ceramic annular runner.

3. The turbine shroud of claim 1 , wherein the plurality of pin receivers are spaced apart from each other circumferentially around the ceramic annular runner.

4. The turbine shroud of claim 1 , wherein turbine shroud comprises at least three insert pins and the ceramic annular runner comprises at least three corresponding pin receivers.

5. The turbine shroud of claim 1 , wherein each of the pin receivers includes an axial dimension and a circumferential dimension and the axial dimension is larger than the circumferential dimension.

6. The turbine shroud of claim 1 , wherein the ceramic annular runner consists essentially of ceramic matrix composite material.

7. The turbine shroud of claim 1 , wherein the ceramic annular runner consists essentially of silicon carbide matrix and silicon carbide fibers.

8. The turbine shroud of claim 1 , wherein the insert pin comprises a metallic material.

9. The turbine shroud of claim 1 , further comprising a seal positioned radially between the annular metallic carrier and the ceramic annular runner.

10. The turbine shroud of claim 1 , wherein the outer radial surface of the ceramic annular runner is formed without radially extending protrusions.

11. The turbine shroud of claim 2 , wherein the outer radial surface defines at least a portion of the forward section, midsection, and aft section.

12. A turbine shroud comprising
a carrier adapted to be coupled to a turbine case,
a solid blade track including a ceramic full-hoop, annular runner and a cylindrical boss that extends radially outward away from the ceramic full-hoop, annular runner and the cylindrical boss formed to include a pin receiver that extends radially inward into the cylindrical boss, and
an insert pin arranged to extend through the carrier into the pin receiver to block rotation of the ceramic annular runner relative to the carrier.

13. The turbine shroud of claim 12 , 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 cylindrical boss is formed in the midsection of the ceramic annular runner.

14. The turbine shroud of claim 12 , wherein the ceramic annular runner consists essentially of ceramic matrix composite material.

15. The turbine shroud of claim 12 , wherein the ceramic annular runner consists essentially of silicon carbide matrix and silicon carbide fibers.

16. The turbine shroud of claim 12 , wherein the insert pin comprises a metallic material.

17. A method of assembling a turbine shroud, the method comprising the steps of
providing a carrier formed to include a plurality of apertures that extend in a radial direction through the carrier, a solid annular runner comprising ceramic matrix composite materials and formed to include pin receivers that extend inwardly in a radial direction partway into the solid ceramic annular runner from an outer radial surface toward an inner radial surface of the solid ceramic annular runner, and a plurality of insert pins,
rotating the solid annular runner to a predetermined orientation relative to the carrier so that the pin receivers formed in the solid annular runner are aligned with the plurality of apertures formed in the carrier,
nesting the solid annular runner into the carrier so that the solid annular runner is concentric with the carrier, and
placing the plurality of insert pins into corresponding apertures and pin receivers to thereby establish a connection between the solid annular runner and the carrier.

18. The method of claim 17 , wherein the solid 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 pin receivers are formed in the midsection of the solid annular runner.

19. The method of claim 17 , wherein the outer radial surface of the solid ceramic annular runner is formed without radially extending protrusions.

20. The method of claim 18 , wherein the outer radial surface defines at least a portion of the forward section, midsection, and aft section.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Sippel Aaron D
• Varney Bruce E
• Freeman Ted J
• Walston Jeffrey A
• Shi Jun

Classifications

• F01D25/005

  Selecting particular materials · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F01D11/08

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

• F01D11/122

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

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title