Impingement tubes for CMC seal segment cooling

Patent metadata

Field	Value
Publication number	US-10100654-B2
Application number	US-201514950794-A
Country	US
Kind code	B2
Filing date	Nov 24, 2015
Priority date	Nov 24, 2015
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

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. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

First claim

What is claimed is:

1. A turbine shroud comprising
a plurality of carrier segments comprising metallic material and arranged circumferentially adjacent to one another around an axis,
a plurality of blade track segments comprising ceramic-matrix composite material and arranged circumferentially adjacent to one another around the axis, each blade track segment coupled to one of the carrier segments, and
a plurality of impingement tubes, each impingement tube extending into one of the carrier segments and configured to direct a flow of cooling air toward a radially-outward facing side of the blade track segment,
wherein each blade track segment includes a runner and at least two attachment features extending radially outward from the runner, the at least two attachment features axially spaced apart from one another and circumferentially extending along the runner, and
wherein each impingement tube is positioned between one of the at least two attachment features and the runner of a corresponding blade track segment.

2. The turbine shroud of claim 1 , wherein each impingement tube includes an elongated body defining an internal plenum, an opening formed through one end of the elongated body and extending into the internal plenum, and an impingement hole formed through the elongated body and in fluid communication with the internal plenum.

3. The turbine shroud of claim 2 , wherein the impingement hole is configured to direct the flow of cooling air toward the radially-outward facing side of the blade track segment at an angle relative to the radially-outward facing side such that the flow of cooling air is not normal to the radially-outward facing side.

4. The turbine shroud of claim 2 , wherein the impingement hole is configured to direct the flow of cooling air toward the radially-outward facing side of the blade track segment such that the flow of cooling air is generally normal to the radially-outward facing side.

5. The turbine shroud of claim 1 , wherein each impingement tube includes an elongated body defining an internal plenum, an opening formed through one end of the elongated body and extending into the internal plenum, and an impingement slot extending along and formed through the elongated body, and the impingement slot is in fluid communication with the internal plenum.

6. The turbine shroud of claim 5 , wherein each impingement tube further includes a constriction positioned between the internal plenum and the opening, the constriction configured to control the flow of cooling air through the impingement tube.

7. The turbine shroud of claim 1 , wherein each carrier segment is formed to include a tube receiver configured to receive one of the impingement tubes to hold the impingement tube in place relative to the carrier segment.

8. The turbine shroud of claim 7 , wherein each carrier segment is further formed to include a tube support aligned with and spaced apart from the tube receiver, the tube support configured to engage a free end of one of the impingement tubes.

9. The turbine shroud of claim 7 , wherein each impingement tube extends axially into the carrier segments through the tube receivers such that an axis extending through the void of each impingement tube is parallel to the axis.

10. A turbine shroud comprising
a plurality of carrier segments comprising metallic material and arranged circumferentially adjacent to one another around an axis,
a plurality of blade track segments comprising ceramic-matrix composite material and arranged circumferentially adjacent to one another around the axis, each blade track segment coupled to one of the carrier segments, and
a plurality of impingement tubes, each impingement tube extending into one of the carrier segments and configured to direct a flow of cooling air toward a radially-outward facing side of the blade track segment,
wherein each blade track segment includes a runner and at least two attachment features extending radially outward from the runner, the at least two attachment features circumferentially spaced apart from one another and axially extending along the runner, and
wherein the spacing between the at least two attachment features is such that the impingement tube blocks removal of the blade track segment when the impingement tube is coupled to the carrier segment.

11. A turbine shroud segment for use in a gas turbine engine, the turbine shroud segment comprising
a carrier segment formed to define an internal cavity,
a blade track segment coupled to the carrier segment to cover an opening into the internal cavity and having an arcuate runner shaped to extend partway around a central axis, and
an impingement tube extending into the internal cavity, the impingement tube configured to direct a flow of cooling air toward a side of the blade track segment that faces the internal cavity,
wherein each carrier segment is formed to include a tube receiver configured to receive one of the impingement tubes to hold the impingement tube in place relative to the carrier segment, and
wherein each impingement tube extends axially into the carrier segments through the tube receivers with a tube axis that extends through a void of each impingement tube, the tube axis being parallel to the central axis.

12. The turbine shroud segment of claim 11 , wherein the blade track segment includes at least two attachment posts extending radially outward from the runner into the internal cavity away from the central axis, the at least two attachment posts circumferentially spaced apart from one another around the central axis and axially extending along the central axis.

13. The turbine shroud segment of claim 12 , wherein each impingement tube extends axially along the central axis into the internal cavity between the at least two attachment posts of the blade track segment.

14. The turbine shroud segment of claim 11 , wherein the impingement tube includes an elongated body defining an internal plenum, an opening formed through one end of the elongated body and extending into the internal plenum, and an impingement hole formed through the elongated body and in fluid communication with the internal plenum.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Plc
• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Vetters Daniel K
• Broadhead Peter
• Hillier Steven

Classifications

• F01D9/06 Primary

  Fluid supply conduits to nozzles or the like · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title