Gas turbine engine turbine nozzle impingement cover

Patent metadata

Field	Value
Publication number	US-9371735-B2
Application number	US-201213689250-A
Country	US
Kind code	B2
Filing date	Nov 29, 2012
Priority date	Nov 29, 2012
Publication date	Jun 21, 2016
Grant date	Jun 21, 2016

Abstract

An impingement cover ( 460 ) for fusing to a gas turbine engine turbine nozzle ( 451 ) with a nozzle rail ( 455 ) includes a body and a plurality of tabs for forming a first fuse with the nozzle rail ( 455 ). The body has a plate like shape and includes a plurality of impingement holes ( 464 ), a first edge, a second edge, and a first airfoil cooling hole ( 470 ). The plurality of tabs includes a first tab ( 461 ) extending from the first edge, and a second tab ( 462 ) extending from the second edge. The second tab ( 462 ) is located in a different quadrant of the body than the first tab ( 461 ).

First claim

What is claimed is:

1. An impingement cover for fusing to a gas turbine engine turbine nozzle with a nozzle rail, the impingement cover comprising:
a body with a plate-like shape divisible into quadrants and having a first edge and a second edge, the body defining a plurality of impingement holes and a first airfoil cooling hole; and
a plurality of tabs for forming a first fuse with the nozzle rail, the plurality of tabs including
a first tab extending from the first edge, and
a second tab extending from the second edge, the second tab being located in a quadrant of the body that is different from a quadrant of the first tab,

a length of the first tab is less than one-third of a length of the first edge, and a length of the second tab is less than one-third of a length of the second edge.

2. The impingement cover of claim 1 , wherein the body has a third edge, and the plurality of tabs includes a third tab extending from the third edge.

3. The impingement cover of claim 1 , wherein the plurality of tabs includes a third tab extending from the second edge.

4. The impingement cover of claim 3 , wherein the first edge is a trailing edge, located proximal to a pressure side of the first airfoil cooling hole, and the second edge is an aft edge located adjacent to the trailing edge.

5. The impingement cover of claim 4 , wherein the body further includes
a forward edge disposed opposite the second edge and adjacent to the first edge, and
a leading edge located opposite the first edge, and
wherein the first tab extends from the first edge proximal to the forward edge, the second tab extends from the second edge proximal to the first edge, and the third tab extends from the second edge proximal to the leading edge.

6. The impingement cover of claim 4 , wherein the first tab is circular in shape, the second tab is trapezoidal in shape, and the third tab is trapezoidal in shape.

7. The impingement cover of claim 1 , wherein the first edge is adjacent to the second edge.

8. The impingement cover of claim 1 , wherein the length of the first tab is less than ten percent of the length of the first edge, and the length of the second tab is less than ten percent of the length of the second edge.

9. A turbine nozzle for a gas turbine engine, the turbine nozzle comprising:
an outer wall having a nozzle rail including
a forward rail,
an aft rail opposite the forward rail,
a leading rail extending between the forward rail and the aft rail, and
a trailing rail extending between the forward rail and the aft rail, and disposed opposite the leading rail;

an inner wall;
an airfoil extending between the outer wall and the inner wall, an interior of the airfoil defining a cooling air path therein; and
an impingement cover having
a plurality of edges including
a forward edge adjacent to the forward rail,
an aft edge adjacent to the aft rail,
a leading edge adjacent to the leading rail and proximal to a suction side of the airfoil, and
a trailing edge adjacent to the trailing rail,

a first tab extending from a first edge of the plurality of edges and fused to the nozzle rail, and
a second tab extending from a second edge of the plurality of edges and fused to the nozzle rail, the second tab being located in a quadrant of the impingement cover that is different from a quadrant of the first tab,

the impingement cover defines a plurality of impingement holes adjacent to the outer wall, and defines a first airfoil cooling hole aligned with the cooling air path,
a length of the first tab is less than one-third of a length of the first edge, and a length of the second tab is less than one-third of a length of the second edge.

10. The turbine nozzle of claim 9 , wherein the first tab and the second tab are fused to the nozzle rail with a first weld and each edge of the plurality of edges is fused to the nozzle rail with a second weld.

11. The turbine nozzle of claim 10 , wherein the first weld is a tack weld and the second weld is a laser weld.

12. The turbine nozzle of claim 9 , wherein the plurality of tabs includes a third tab extending from one edge of the plurality of edges.

13. The turbine nozzle of claim 12 , wherein the first tab extends from the trailing edge proximal to the forward edge, the second tab extends from the aft edge proximal to the trailing edge, and the third tab extends from the aft edge proximal to the leading edge.

14. The turbine nozzle of claim 13 , wherein the first tab is tack welded to the trailing rail, the second tab is tack welded to the aft rail, and the third tab is tack welded to the aft rail.

15. The turbine nozzle of claim 14 , wherein the forward edge is laser welded to the forward rail, the aft edge is laser welded to the aft rail, the leading edge is laser welded to the leading rail, and the trailing edge is laser welded to the trailing rail.

16. The turbine nozzle of claim 15 , wherein each edge of the impingement cover is spaced apart from the nozzle rail from 0.020″ to 0.040″.

17. The turbine nozzle of claim 9 , wherein the length of the first tab and the length of the second tab are each less than ten percent of a length of one edge of the plurality of edges.

18. A gas turbine engine including a plurality of the turbine nozzles of claim 9 , wherein the plurality of turbine nozzles form a turbine nozzle stage.

19. A method for joining an impingement cover to a gas turbine engine turbine nozzle, the method comprising:
placing an impingement cover within a nozzle rail of the turbine nozzle, the impingement cover having a first tab extending from a first edge and a second tab extending from a second edge;
fusing the first tab and the second tab to the nozzle rail; and
fusing the first edge and the second edge to the nozzle rail,
a length of the first tab being less than one-third of a length of the first edge, and a length of the second tab being less than one-third of a length of the second edge.

20. The method of claim 19 , wherein the fusing the first tab and the second tab to the nozzle rail includes welding the first tab and the second tab to the nozzle rail, and
wherein the fusing the first edge and the second edge to the nozzle rail includes welding the first edge and the second edge to the nozzle rail.

Assignees

• Solar Turbines Inc

Inventors

• Reilly William Landon
• Jeorling David
• Reyes Adrian Nazareno

Classifications

• F05D2230/232

  by welding · CPC title

• F01D9/041 Primary

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

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title