Turbine shroud segment with integrated cooling air distribution system

• US 10,184,352 B2
• Filed: 01/22/2016
• Issued: 01/22/2019
• Est. Priority Date: 06/29/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: O'Leary, Mark, Vetters, Daniel K., Brandt, Matthew R., Freeman, Ted J.
• Primary Examiner(s): Brockman, Eldon
• Application Number:
  US15/004,436
• Publication Number:
  US 20160376921A1
• Time in Patent Office: 1,096 Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 11/20 Actively adjusting tip-clearance
• CPC Class Codes: F01D 25/005 Selecting particular materials
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Claims

1. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment formed to include an attachment-receiving space,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend at least partway around a central axis and an attachment box portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and

an attachment assembly including an attachment post that extends from the carrier segment into the attachment box portion of the blade track segment, the attachment post formed to include a post passageway that provides part of a cooling system configured to conduct cooling air into the attachment box portion of the blade track segment to cool the blade track segment when the turbine shroud segment is used in a gas turbine engine, wherein the attachment box portion included in the blade track segment defines a box interior bounded by a radially-outwardly facing surface of the runner included in the blade track segment so that cooling air conducted into the box interior by the post passageway cools the radially-outwardly facing surface of the runner, and wherein the box interior defined by the attachment box portion of the blade track segment is open for fluid communication with the attachment-receiving space formed by the carrier segment and the carrier segment is formed to include a plurality of vent holes configured to conduct used cooling air out of the attachment-receiving space.

2. The turbine shroud segment of claim 1, wherein the distribution passageways extend axially along the central axis and circumferentially around the central axis.

3. The turbine shroud segment of claim 1, wherein the attachment post extends into the attachment box portion of the blade track segment through an attachment hole formed in the attachment box portion and the attachment support is sized to block withdrawal of the attachment post out of the attachment box portion.

4. The turbine shroud segment of claim 1, wherein the attachment post includes a shaft and support threads formed on the shaft that engage the attachment support to couple the attachment post to the attachment support.

5. The turbine shroud segment of claim 1, wherein the distribution passageways formed by the attachment support are arranged to discharge cooling air at various locations toward a radially-outwardly facing surface of the runner included in the blade track segment.

6. The turbine shroud segment of claim 1, wherein the attachment post extends through a post hole formed in the carrier segment into the attachment-receiving space formed by the carrier segment and through an attachment hole formed in the attachment box portion of the blade track segment.

7. The turbine shroud segment of claim 1, wherein the plurality of vent holes are arranged along an aft side of the carrier segment.

8. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment formed to include an attachment-receiving space,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend at least partway around a central axis and an attachment box portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and

an attachment assembly including an attachment post that extends from the carrier segment into the attachment box portion of the blade track segment, the attachment post formed to include a post passageway that provides part of a cooling system configured to conduct cooling air into the attachment box portion of the blade track segment to cool the blade track segment when the turbine shroud segment is used in a gas turbine engine,

wherein the carrier segment is formed to include an inlet passageway fluidly coupled to the post passageway formed in the attachment post so that cooling air introduced into the inlet passageway is conducted through the post passageway into the attachment box portion of the blade track segment when the turbine shroud segment is used in a gas turbine engine.

9. The turbine shroud segment of claim 8, wherein the attachment box portion included in the blade track segment defines a box interior bounded by a radially-outwardly facing surface of the runner included in the blade track segment so that cooling air conducted into the box interior by the post passageway cools the radially-outwardly facing surface of the runner, and wherein the box interior defined by the attachment box portion of the blade track segment is open for fluid communication with the attachment-receiving space formed by the carrier segment and the carrier segment is formed to include a plurality of vent holes configured to conduct used cooling air out of the attachment-receiving space.

10. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment formed to include an attachment-receiving space,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend at least partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and

an attachment assembly including an attachment post that extends from the carrier segment through an attachment hole formed in the attachment portion of the blade track segment and an attachment support coupled to the attachment post to block withdrawal of the attachment post through the attachment hole, wherein the carrier segment is formed to include a plurality of vent holes that extend out of the attachment-receiving space configured to conduct used cooling air out of the attachment-receiving space.

11. The turbine shroud segment of claim 10, wherein the attachment post includes a shaft and support threads formed on the shaft that engage the attachment support to couple the attachment post to the attachment support.

12. The turbine shroud segment of claim 10, wherein the attachment support is shaped to extend at least partway around the central axis.

13. The turbine shroud segment of claim 12, wherein the distribution passageways extend axially along the central axis and circumferentially around the central axis.

14. The turbine shroud segment of claim 12, wherein the distribution passageways formed by the attachment support are arranged to discharge cooling air at various locations toward a radially-outwardly facing surface of the runner included in the blade track segment.

15. The turbine shroud segment of claim 10, wherein the attachment post extends through a post hole formed in the carrier segment into the attachment-receiving space formed by the carrier segment.

16. The turbine shroud segment of claim 15, wherein the carrier segment is formed to include an inlet passageway fluidly coupled to the post passageway formed in the attachment post.

17. The turbine shroud of claim 10, wherein the plurality of vent holes are arranged along an aft side of the carrier segment.