Turbine nozzle assembly and gas turbine including the same

Patent metadata

Field	Value
Publication number	US-11608754-B2
Application number	US-202117375595-A
Country	US
Kind code	B2
Filing date	Jul 14, 2021
Priority date	Jul 14, 2021
Publication date	Mar 21, 2023
Grant date	Mar 21, 2023

Abstract

A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner diameter to an outer diameter and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a hollow airfoil including a plurality of cavities positioned in the airfoil, an insert positioned in one or more of the plurality of cavities of the hollow airfoil, a plurality of cover plates, at least one of which is positioned at one of the inner diameter and at the outer diameter, and a plurality of impingement pans, at least one of which is positioned at one of the inner diameter and at the outer diameter.

First claim

What is claimed is:

1. A turbine nozzle assembly of a turbine comprising:
a turbine nozzle extending from an inner diameter to an outer diameter and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge,
wherein the turbine nozzle comprises:
a hollow airfoil including a plurality of cavities positioned in the airfoil;
an insert positioned in one or more of the plurality of cavities of the hollow airfoil;
a plurality of cover plates, at least one of which is positioned at the inner diameter and at least one of which is positioned at the outer diameter; and
a plurality of impingement pans, at least one of which is positioned at the inner diameter and at least one of which is positioned at the outer diameter,
wherein the cover plate of the inner diameter covers a first pocket, and the cover plate of the outer diameter covers a second pocket, wherein the first pocket arranged to form a first recessed area within the inner diameter at the trailing edge portion of the airfoil includes a first opening facing radially inward relative to a central axis of the turbine, and the second pocket arranged to form a second recessed area within the outer diameter at the trailing edge portion of the airfoil includes a second opening facing radially outward relative to the central axis of the turbine.

2. The turbine nozzle assembly according to claim 1 , further comprising cooling holes positioned at the leading edge of the airfoil.

3. The turbine nozzle assembly according to claim 2 , wherein the cooling holes have a bilaterally symmetrical pattern.

4. The turbine nozzle assembly according to claim 1 , wherein the insert has a pipe-type shape.

5. The turbine nozzle assembly according to claim 4 , wherein the inserts include a plurality of through holes formed in a surface thereof.

6. The turbine nozzle assembly according to claim 4 , wherein the insert has a cross-sectional shape similar to a cross-sectional shape of the cavity in a radially transverse direction, resulting in a structure in which an annular space formed between an inner surface of the airfoil and an outer surface of the insert in the cavity has a uniform width.

7. The turbine nozzle assembly according to claim 1 , wherein the plurality of cavities is defined by a plurality of ribs.

8. The turbine nozzle assembly according to claim 1 , wherein the plurality of cover plates are recessed cover plates.

9. The turbine nozzle assembly according to claim 1 , wherein the impingement pans include a plurality of through holes formed in a surface thereof.

10. A turbine nozzle assembly of a turbine comprising:
a hollow airfoil having a leading edge, a trailing edge, sidewalls between the leading edge and the trailing edge, and inner and outer diameters disposed at opposite ends of the airfoil to support the airfoil, a plurality of cavities being defined within the airfoil and a plurality of cooling holes being defined in the leading edge of the airfoil;
an insert positioned in one or more of the plurality of cavities of the hollow airfoil;
a plurality of cover plates, at least one of which is positioned at the inner diameter and at least one of which is positioned at the outer diameter; and
a plurality of impingement pans, at least one of which is positioned at the inner diameter and at least one of which is positioned at the outer diameter,
wherein the cover plate of the inner diameter covers a first pocket, and the cover plate of the outer diameter covers a second pocket, wherein the first pocket arranged to form a first recessed area within the inner diameter at the trailing edge portion of the airfoil includes a first opening facing radially inward relative to a central axis of the turbine, and the second pocket arranged to form a second recessed area within the outer diameter at the trailing edge portion of the airfoil includes a second opening facing radially outward relative to the central axis of the turbine.

11. The turbine nozzle assembly according to claim 10 , wherein the plurality of cooling holes positioned in the leading edge of the airfoil have a bilaterally symmetrical pattern.

12. The turbine nozzle assembly according to claim 10 , wherein the insert has a pipe-type shape.

13. The turbine nozzle assembly according to claim 12 , wherein the insert includes a plurality of through holes formed in a surface thereof.

14. The turbine nozzle assembly according to claim 10 , wherein the cover plate is a recessed cover plate.

15. The turbine nozzle assembly according to claim 10 , wherein the impingement pans include a plurality of through holes formed in a surface thereof.

16. A gas turbine comprising:
a compressor configured to compress air;
a combustor configured to mix compressed air supplied from the compressor with fuel for combustion to generate combustion gas; and
a turbine comprising a plurality of turbine nozzles and a plurality of turbine blades rotated by the combustion gas to generate power,
wherein each of the turbine nozzles extends from an inner diameter to an outer diameter and has an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, and
wherein the turbine nozzle comprises:
a hollow airfoil including a plurality of cavities positioned in the airfoil;
an insert positioned in one or more of the plurality of cavities of the hollow airfoil;
a plurality of cover plates, at least one of which is positioned at the inner diameter and at least one of which is positioned at the outer diameter;
a plurality of impingement pans, at least one of which is positioned at the inner diameter and at least one of which is positioned at the outer diameter; and
a plurality of cooling holes positioned at the leading edge of the airfoil and having a bilaterally symmetrical pattern,
wherein the cover plate of the inner diameter covers a first pocket, and the cover plate of the outer diameter covers a second pocket, wherein the first pocket arranged to form a first recessed area within the inner diameter at the trailing edge portion of the airfoil includes a first opening facing radially inward relative to a central axis of the gas turbine, and the second pocket arranged to form a second recessed area within the outer diameter at the trailing edge portion of the airfoil includes a second opening facing radially outward relative to the central axis of the gas turbine.

17. The gas turbine according to claim 16 , wherein the insert has a pipe-type shape and includes a plurality of through holes formed in a surface thereof.

18. The gas turbine according to claim 16 , wherein the plurality of cover plates are recessed cover plates.

Assignees

• Doosan Enerbility Co Ltd

Inventors

• Chong Gene
• Kim Yejee
• Eng Darryl
• Day David
• Mun Younggi
• Bernier Bryan
• Seo Hongseung
• Lee Jaebin

Classifications

• F01D25/12 Primary

  Cooling · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/188

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

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/32

  in gas turbines · CPC title