Turbine nozzle with inner band and outer band cooling

Patent metadata

Field	Value
Publication number	US-2017101890-A1
Application number	US-201514880565-A
Country	US
Kind code	A1
Filing date	Oct 12, 2015
Priority date	Oct 12, 2015
Publication date	Apr 13, 2017
Grant date	—

Abstract

A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define outer flow boundaries of the turbine nozzle. The inner band includes a gas side surface that is at least partially covered by one or more inner plates. The inner band also includes a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates. The outer band includes a gas side surface that is at least partially covered by one or more outer plates. The outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.

First claim

What is claimed is:

1 . A turbine nozzle, comprising:
an airfoil that extends in span from an inner band to an outer band, the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle; wherein the inner band has a gas side surface at least partially covered by one or more inner plates, wherein the inner band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates; and wherein the outer band has a gas side surface at least partially covered by one or more outer plates, wherein the outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.

2 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the outer band comprises at least one serpentine shaped cooling channel.

3 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the outer band comprises at least one serpentine shaped cooling channel defined between a leading edge portion of the airfoil and a forward wall of the outer band.

4 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the outer band comprises at least one serpentine shaped cooling channel defined between a pressure side wall of the airfoil and a pressure side wall of the outer band.

5 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the inner band comprises at least one serpentine shaped cooling channel.

6 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the inner band comprises at least one serpentine shaped cooling channel defined between a leading edge portion of the airfoil and a forward wall of the inner band.

7 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the inner band comprises at least one serpentine shaped cooling channel defined between a pressure side wall of the airfoil and a pressure side wall of the outer band.

8 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the inner band comprises at least one cooling channel disposed along a leading edge portion of the inner band and extending between a pressure side wall and a suction side wall of the inner band.

9 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the outer band comprises a group of densely spaced cooling channels and a group of sparsely spaced cooling channels.

10 . The turbine nozzle as in claim 1 , wherein the plurality of cooling channels of the inner band comprises a group of densely spaced cooling channels and a group of sparsely spaced cooling channels.

11 . A gas turbine, comprising:
a compressor; a combustor downstream from the compressor; and a turbine disposed downstream from the combustor, wherein the turbine comprises a stage having a row of turbine nozzles and a row of turbine rotor blades, at least one turbine nozzle comprising:
an airfoil that extends in span from an inner band to an outer band, wherein the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle;
wherein the inner band has a gas side surface at least partially covered by one or more inner plates, wherein the inner band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates; and
wherein the outer band has a gas side surface at least partially covered by one or more outer plates, wherein the outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.

12 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the outer band comprises at least one serpentine shaped cooling channel.

13 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the outer band comprises at least one serpentine shaped cooling channel defined between a leading edge portion of the airfoil and a forward wall of the outer band.

14 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the outer band comprises at least one serpentine shaped cooling channel defined between a pressure side wall of the airfoil and a pressure side wall of the outer band.

15 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the inner band comprises at least one serpentine shaped cooling channel.

16 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the inner band comprises at least one serpentine shaped cooling channel defined between a leading edge portion of the airfoil and a forward wall of the inner band.

17 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the inner band comprises at least one serpentine shaped cooling channel defined between a pressure side wall of the airfoil and a pressure side wall of the outer band.

18 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the inner band comprises at least one cooling channel disposed along a leading edge portion of the inner band and extending between a pressure side wall and a suction side wall of the inner band.

19 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the outer band comprises a group of densely spaced cooling channels and a group of sparsely spaced cooling channels.

20 . The gas turbine as in claim 11 , wherein the plurality of cooling channels of the inner band comprises a group of densely spaced cooling channels and a group of sparsely spaced cooling channels.

Assignees

• Gen Electric

Inventors

• Dutta Sandip
• Lacy Benjamin Paul
• Weber Joseph Anthony
• Stevens Peter Galen

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title