Impingement tubes for gas turbine engine assemblies with ceramic matrix composite components

Patent metadata

Field	Value
Publication number	US-11002143-B2
Application number	US-201816136866-A
Country	US
Kind code	B2
Filing date	Sep 20, 2018
Priority date	Nov 24, 2015
Publication date	May 11, 2021
Grant date	May 11, 2021

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 engine assembly, the assembly comprising
a carrier component comprising metallic material,
a supported component comprising ceramic-matrix composite material coupled to the carrier component, the supported component including a runner that extends partway around a central axis and at least two attachment features extending radially outward relative to the central axis from the runner, the at least two attachment features axially spaced apart from one another and circumferentially extending along the runner around the central axis, and
a plurality of impingement tubes, each impingement tube extending into the carrier component and configured to direct a flow of cooling air toward a radially-outward facing side of the supported component, each impingement tube positioned between one of the at least two attachment features and the runner of the supported component.

2. The assembly 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 assembly of claim 2 , wherein the impingement hole is configured to direct the flow of cooling air toward the radially-outward facing side of the supported component 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 assembly of claim 2 , wherein the impingement hole is configured to direct the flow of cooling air toward the radially-outward facing side of the supported component such that the flow of cooling air is generally normal to the radially-outward facing side.

5. The assembly 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 assembly 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 assembly of claim 1 , wherein the carrier component is formed to include a tube receiver configured to receive one of the impingement tubes included in the plurality of impingement tubes to hold the one of the impingement tubes in place relative to the carrier component.

8. The assembly of claim 7 , wherein the carrier component 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 included in the plurality of impingement tubes.

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

10. A turbine engine assembly, the assembly comprising
a carrier component comprising metallic material,
a supported component comprising ceramic-matrix coupled to the carrier component, the supported component including a runner that extends partway around a central axis and at least two attachment features extending radially outward relative to the central axis from the runner, and
an impingement tube extending into the carrier component and configured to direct a flow of cooling air toward a radially-outward facing side of the supported component, wherein the spacing between the at least two attachment features is such that the impingement tube blocks removal of the supported component when the impingement tube is coupled to the carrier component.

11. The assembly of claim 10 , wherein the at least two attachment features are circumferentially spaced apart from one another and axially extending along the runner.

12. The assembly of claim 10 , wherein the at least two attachment features are provided by spaced apart attachment posts and attachment pins that extend from the attachment posts to engagement with the carrier component to couple the supported component to the carrier component.

13. The assembly of claim 12 , wherein the attachment pins extend through the attachment posts.

14. A gas turbine engine assembly, the assembly comprising
a carrier component formed to define an internal cavity,
a supported component coupled to the carrier component including 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 supported component that faces the internal cavity, the impingement tube arranged to extend axially into the carrier component along the central axis with a tube axis that extends through a void of the impingement tube, the tube axis being parallel to the central axis.

15. The assembly of claim 14 , wherein the carrier component is formed to include a tube receiver configured to receive the impingement tube to hold the impingement tube in place relative to the carrier component.

16. The assembly of claim 14 , wherein the supported component includes at least two attachment posts extending radially outward from the runner into the internal cavity away from the central axis.

17. The assembly of claim 16 , wherein the at least two attachment posts extend along the central axis.

18. The assembly of claim 16 , wherein the at least two attachment posts are circumferentially spaced apart from one another around the central axis.

19. The assembly of claim 18 , wherein the impingement tube extends axially along the central axis into the internal cavity between the at least two attachment posts of the supported component.

20. The assembly of claim 14 , 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

Inventors

• Vetters Daniel K
• Broadhead Peter
• Hillier Steven

Classifications

• F01D11/08 Primary

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

• F01D25/12

  Cooling · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2240/11

  Shroud seal segments · CPC title