Annular ring assembly for shroud cooling

Patent metadata

Field	Value
Publication number	US-9689276-B2
Application number	US-201414335289-A
Country	US
Kind code	B2
Filing date	Jul 18, 2014
Priority date	Jul 18, 2014
Publication date	Jun 27, 2017
Grant date	Jun 27, 2017

Abstract

A gas turbine engine includes an annular casing and a plurality of shroud segments forming an annular shroud. The annular shroud forms with the annular casing an annular cavity therebetween. The annular cavity includes an inlet and an outlet. An annular ring assembly is disposed in the annular cavity between the casing and the shroud and cooperating therewith to provide a first annular chamber and a second annular chamber. The annular ring assembly and a first portion of the shroud form the first annular chamber. The annular ring assembly and a second portion of the shroud form the second annular chamber. The annular ring assembly forms an intermediate annular chamber disposed between the first annular chamber and the second annular chamber. A flow path for coolant air is sequentially defined through the inlet, the first annular chamber, the intermediate annular chamber, the second annular chamber and the outlet.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
an annular shroud encircling one of a stator and a rotor, the shroud having a first portion and a second portion axially disposed downstream of the first portion of the shroud relative to a rotation axis of the engine and a direction of airflow through the rotor in use;
an annular casing outwardly spaced-apart from the shroud and mounted thereto to define an annular cavity between the casing and the shroud, the cavity including an inlet communicating with a source of coolant air and an outlet communicating with gas path;
an annular ring assembly disposed in the cavity between the casing and the shroud and configured to cooperate with the casing and the shroud, the annular ring assembly and the first portion of the shroud forming a first annular chamber by abutment surfaces of annular shape circumferentially formed between the annular shroud and the annular ring such that the first annular chamber is enclosed between the first portion of the shroud, the annular ring assembly and the abutment surfaces, the annular ring assembly and the second portion of the shroud forming a second annular chamber, the ring forming an intermediate annular chamber disposed between the first annular chamber and the second annular chamber, the annular ring assembly having:
a non-diffusive wall preventing coolant incoming from the inlet to reach the second portion of the shroud and directing the coolant toward the first annular chamber;
an annular impingement body having:
a first surface facing the shroud; and
an opposed second surface facing the casing; and
an annular dividing body connected to the second surface of the impingement body and forming therewith the intermediate annular chamber,
the annular ring assembly having a plurality of first impingement apertures for distributing coolant from the inlet to the first portion of the shroud and a plurality of second impingement apertures for distributing coolant from the intermediate annular chamber to the second portion of the shroud, the first chamber communicating with the intermediate annular chamber via at least one intermediate aperture disposed between the plurality of first impingement apertures and the plurality of second impingement apertures, the annular ring assembly thus providing a coolant flow path sequentially from the inlet, through the first annular chamber, the intermediate annular chamber, the second annular chamber and the outlet.

2. The gas turbine engine of claim 1 , wherein a first portion of the first surface of the impingement body forms with the first portion of the shroud the first annular chamber, a second portion of the first surface of the impingement body forms with the second portion of the shroud the second annular chamber, the first portion includes the plurality of first impingement apertures, and the second portion includes the plurality of second impingement apertures.

3. The gas turbine engine of claim 1 , wherein the annular ring assembly is secured in compression between the shroud and the casing.

4. The gas turbine engine of claim 1 , wherein the dividing body has one end fixedly connected to the second surface of the annular impingement body, and one end radially displaceable relative to the annular impingement body.

5. The gas turbine engine of claim 1 , wherein the shroud includes a circumferential rib defining a separation between the first and second annular chambers.

6. The gas turbine engine of claim 1 , wherein the shroud includes a plurality of shroud segments, the annular ring assembly extending through the plurality of shroud segments.

7. The gas turbine engine of claim 1 , wherein the plurality of first impingement apertures are distributed onto a curved L-shaped portion of the impingement body.

8. The gas turbine engine of claim 1 , wherein the dividing body includes the non-diffusive wall.

9. The gas turbine engine of claim 8 , wherein the dividing body has an inverted U-shaped portion including a first radial branch, an axial branch, and a second radial branch, the first radial branch defining the non-diffusive wall, the second radial branch including a plurality of apertures.

10. The gas turbine engine of claim 1 , wherein the impingement body is monolithic.

11. The gas turbine engine of claim 1 , wherein the dividing body is monolithic.

12. The gas turbine engine of claim 1 , wherein the plurality of first impingement apertures define an inlet area to the first chamber, and the at least one intermediate aperture defines an outlet area of the first chamber, the outlet area being smaller than the inlet area.

13. A gas turbine engine comprising:
an annular casing;
a plurality of shroud segments forming an annular shroud, each shroud segment defining an angular portion of the annular shroud, the annular shroud forming with the annular casing an annular cavity therebetween, the annular cavity including an inlet and an outlet; and
an annular ring assembly disposed in the annular cavity between the casing and the shroud and cooperating therewith to provide a first annular chamber and a second annular chamber, the annular ring assembly and a first portion of the shroud forming the first annular chamber by abutment surfaces of annular shape formed circumferentially between the annular shroud and the annular ring such that the first annular chamber is enclosed between the first portion of the shroud, the annular ring assembly and the abutment surfaces, the annular ring assembly and a second portion of the shroud forming the second annular chamber, the annular ring assembly forming an intermediate annular chamber disposed between the first annular chamber and the second annular chamber, a flow path for coolant air being sequentially defined through the inlet, the first annular chamber, the intermediate annular chamber, the second annular chamber and the outlet.

14. The gas turbine engine of claim 13 , wherein the annular ring assembly includes:
a plurality of first impingement apertures distributing coolant from the inlet to the first portion of the shroud; and
a plurality of second impingement apertures distributing coolant from the intermediate annular chamber to the second portion of the shroud; and
at least one intermediate aperture disposed axially between the pluralities of first and second impingement apertures, the first annular chamber fluidly communicating with the intermediate annular chamber via the at least one intermediate aperture.

15. The gas turbine engine of claim 14 , wherein the plurality of first impingement apertures define an inlet area to the first chamber, and the at least one intermediate aperture defines an outlet area of the first chamber, the outlet area being smaller than the inlet area.

16. The gas turbine engine of claim 13 , wherein the annular ring assembly includes an annular impingement body having a flat axial portion, the flat axial portion having a first surface facing the shroud and an opposed second surface facing the casing; and
an annular dividing body connected to the second surface of the annular impingement body, the annular dividing body including a U-shaped portion, the U-shaped portion and the second surface of the flat axial portion of the impingement body forming the intermediate chamber.

17. The gas turbine engine of claim 16 , wherein the annular dividing body has one end fixedly connected to the second surface of the annular impingement body, and one end radially displaceable relative to the annular impingement body.

18. The gas turbine engine of claim 13 , wher

Assignees

• Pratt & Whitney Canada

Inventors

• Lefebvre Guy
• Paquet Rene

Classifications

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D25/14

  Casings modified therefor (double casings F01D25/26) · CPC title