Cooling assembly for a gas turbine system

Patent metadata

Field	Value
Publication number	US-9670785-B2
Application number	US-201213451053-A
Country	US
Kind code	B2
Filing date	Apr 19, 2012
Priority date	Apr 19, 2012
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.

First claim

The invention claimed is:

1. A cooling assembly for a gas turbine system comprising:
a turbine nozzle extending between opposite first and second end portions configured to mount in a hot gas path between a turbine casing and a central structure, wherein the turbine nozzle is configured to route a cooling flow only from the first end portion to the second end portion, the turbine nozzle comprises at least one channel comprising a channel inlet in the first end portion configured to receive a the cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet in the second end portion;
a hood surrounding an exit cavity and configured to fluidly connect the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure, wherein the hood is configured to mount in a space between inner and outer casing walls of the turbine casing, and the hood turns from a radially outward direction to a direction along the hot gas path from the channel outlet to the turbine component.

2. The cooling assembly of claim 1 , wherein the cooling source is a compressor disposed upstream of the turbine nozzle and the cooling flow is impinged on the at least one channel.

3. The cooling assembly of claim 2 , wherein the turbine nozzle is disposed between and operably connected to a radially inner segment of the central structure and a radially outer segment of the inner casing wall of the turbine casing.

4. The cooling assembly of claim 3 , wherein the channel inlet is disposed proximate the radially inner segment, wherein the cooling flow is directed radially outward to the channel outlet.

5. The cooling assembly of claim 1 , wherein the turbine nozzle structurally separates the at least one channel from the hot gas path and blocks the cooling flow from entering the hot gas path.

6. The cooling assembly of claim 1 , wherein the turbine shroud assembly is a first stage turbine shroud assembly disposed radially outward of a first turbine rotor stage.

7. The cooling assembly of claim 1 , wherein the turbine nozzle comprises a plurality of paths comprising a serpentine cooling circuit, wherein the channel inlet is disposed proximate at least one of the plurality of paths, wherein the cooling flow is directed radially outward to the channel outlet, wherein the turbine component comprises a turbine shroud assembly disposed downstream of the channel outlet of the turbine nozzle, wherein the exit cavity is enclosed by the hood and directs the cooling flow to an interior region proximate a forward face of the turbine shroud assembly.

8. The cooling assembly of claim 1 , wherein the turbine nozzle is mounted to a radially outer segment, wherein the channel inlet is disposed proximate a post-impingement region and the cooling flow is directed radially outward to the channel outlet.

9. The cooling assembly of claim 1 , wherein the first end portion is coupled to the central structure, and the second end portion is coupled to the turbine casing.

10. The cooling assembly of claim 1 , wherein the turbine nozzle comprises a plurality of paths comprising a serpentine cooling circuit, wherein the channel inlet is disposed proximate at least one of the plurality of paths, wherein the cooling flow is directed radially outward to the channel outlet.

11. A cooling assembly for a gas turbine system comprising:
a hot gas path between a turbine casing and a central structure, wherein the hot gas path is disposed about the central structure, the turbine casing comprises an inner casing wall disposed about the hot gas path and an outer casing wall disposed about the inner casing wall, and the inner casing wall comprises a turbine shroud assembly;
a turbine nozzle extending between opposite first and second end portions, wherein the turbine nozzle is disposed in the hot gas path between the turbine casing and the central structure, wherein the turbine nozzle comprises a plurality of channels each comprising a channel inlet in the first end portion configured to receive a cooling flow from a cooling source, wherein the plurality of channels directs the cooling flow through the turbine nozzle in a only one radial direction to at least one channel outlet in the second end portion;
a plurality of rotor blades rotatably disposed in the hot gas path between the turbine casing and the central structure, wherein the plurality of blades are disposed adjacent the turbine shroud assembly; and;
a hood surrounding an exit cavity and fluidly connecting the channel outlet to the turbine shroud assembly, wherein the hood is configured to route the cooling flow to the turbine shroud assembly, the hood is disposed in a space between the inner and outer casing walls of the turbine casing, and the hood turns from a radially outward direction to a direction along the hot gas path from the channel outlet to the turbine shroud assembly.

12. The cooling assembly of claim 11 , wherein the cooling source comprises a compressor disposed upstream of the turbine nozzle and the cooling flow is impinged on the plurality of channels at a first pressure.

13. The cooling assembly of claim 11 , wherein the first end portion is coupled to the central structure, and the second end portion is coupled to the turbine casing.

14. The cooling assembly of claim 11 , wherein the channel inlet is disposed proximate the radially inner segment of the central structure, wherein the cooling flow is directed radially outward to the channel outlet.

15. The cooling assembly of claim 12 , wherein the exit cavity directs the cooling flow to an interior region proximate a forward face of the turbine shroud assembly, wherein the interior region comprises a second pressure that is less than the first pressure.

16. The cooling assembly of claim 11 , wherein the turbine shroud assembly is a first stage turbine shroud assembly.

17. The cooling assembly of claim 1 , wherein the hood gradually decreases in width in a downstream direction from the channel outlet to the region of the turbine component.

Assignees

• Johns David Richard
• Kirtley Kevin Richard
• Gen Electric

Inventors

• Johns David Richard
• Kirtley Kevin Richard

Classifications

• F05D2250/185

  serpentine-like · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F05D2240/81

  Cooled platforms · CPC title