Nozzle cooling system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10260356-B2
Application number	US-201615171172-A
Country	US
Kind code	B2
Filing date	Jun 2, 2016
Priority date	Jun 2, 2016
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

The present disclosure is directed to a nozzle cooling system for a gas turbine engine. An impingement plate is positioned radially inwardly from a radially inner surface of an inner side wall of a nozzle. The impingement plate and the inner side wall collectively define an inner chamber. The impingement plate includes a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures. A duct plate encloses the first portion of the impingement plate. The duct plate, the first portion of the impingement plate, and inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures. Compressed air from the outer chamber flows through the one or more impingement apertures into the inner chamber and exits the inner chamber through the one or more post-impingement apertures.

First claim

What is claimed is:

1. A nozzle cooling system for a gas turbine engine, comprising:
a nozzle comprising an inner side wall and an airfoil coupled to the inner side wall, the inner side wall comprising a radially inner surface and a radially outer surface, the airfoil defining an airfoil passage;
an impingement plate positioned radially inwardly from the radially inner surface of the inner side wall, the impingement plate and the inner side wall collectively defining an inner chamber, wherein the impingement plate comprises a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures; and
a duct plate enclosing the first portion of the impingement plate, wherein the duct plate, the first portion of the impingement plate, and inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures, the outer chamber further being in fluid communication with the airfoil passage;
wherein compressed air enters the outer chamber through the airfoil passage, the compressed air then flowing from the outer chamber through the one or more impingement apertures into the inner chamber and exiting the inner chamber through the one or more post-impingement apertures.

2. The nozzle cooling system of claim 1 , wherein the nozzle comprises an outer side wall, the airfoil extending from the outer side wall to the inner side wall.

3. The nozzle cooling system of claim 1 , wherein the compressed air exiting the one or more post-impingement apertures flows into a diaphragm cavity.

4. The nozzle cooling system of claim 1 , wherein the duct plate defines one or more outlet apertures that provide fluid communication between the outer chamber and a diaphragm cavity.

5. The nozzle cooling system of claim 4 , wherein the one or more outlet apertures are circumferentially spaced apart from the one or more impingement apertures and the one or more post-impingement apertures.

6. The nozzle cooling system of claim 5 , wherein the airfoil is positioned circumferentially between the one or more outlet apertures and the one or more impingement apertures.

7. The nozzle cooling system of claim 1 , wherein the first portion of the impingement plate comprises a greater area than the second portion of the impingement plate.

8. The nozzle cooling system of claim 1 , wherein the impingement plate is at least partially spaced apart from the radially inner surface of the inner side wall by one or more posts.

9. The nozzle cooling system of claim 1 , wherein the impingement plate comprises a curvilinear surface.

10. The nozzle cooling system of claim 1 , wherein the one or more impingement apertures are positioned axially between the one or more post-impingement apertures and an aft surface of the inner side wall.

11. The nozzle cooling system of claim 1 , wherein the impingement plate is formed from sheet metal.

12. A gas turbine engine, comprising:
a compressor section;
a combustion section; and
a turbine section, comprising:
a nozzle comprising an inner side wall, an outer side wall, and an airfoil extending between the inner side wall and the outer side wall, wherein the inner side wall comprises a radially inner surface and a radially outer surface, the airfoil defining an airfoil passage;
an impingement plate positioned radially inwardly from the radially inner surface of the inner side wall, the impingement plate and the inner side wall collectively defining an inner chamber, wherein the impingement plate comprises a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures; and
a duct plate enclosing the first portion of the impingement plate, wherein the duct plate, the first portion of the impingement plate, and the inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures, the outer chamber further being in fluid communication with the airfoil passage;
wherein compressed air enters the outer chamber through the airfoil passage, the compressed air then flowing from the outer chamber through the one or more impingement apertures into the inner chamber and exiting the inner chamber through the one or more post-impingement apertures.

13. The gas turbine engine of claim 12 , wherein the compressed air exiting the one or more post-impingement apertures flows into a diaphragm cavity.

14. The gas turbine engine of claim 12 , wherein the duct plate defines one or more outlet apertures that provide fluid communication between the outer chamber and a diaphragm cavity.

15. The gas turbine engine of claim 14 , wherein the one or more outlet apertures are circumferentially spaced apart from the one or more impingement apertures and the one or more post-impingement apertures.

16. The gas turbine engine of claim 15 , wherein the airfoil is positioned circumferentially between the one or more outlet apertures and the one or more impingement apertures.

17. The gas turbine engine of claim 12 , wherein the first portion of the impingement plate comprises a greater area than the second portion of the impingement plate.

18. The gas turbine engine of claim 12 , wherein the impingement plate is at least partially spaced apart from the radially inner surface of the inner side wall by one or more posts.

Assignees

• Gen Electric

Inventors

• Gaulden Travis Michael
• Itzel Gary Michael
• Meyer Robert Carl

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/041

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

• F01D25/12 Primary

  Cooling · CPC title

• F01D5/087

  in the radial passages of the rotor disc · CPC title