TURBINE NOZZLE OUTER BAND AND AIRFOIL COOLING APPARATUS

• US 20130309079A1
• Filed: 10/26/2012
• Published: 11/21/2013
• Est. Priority Date: 04/27/2012
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Correia, Victor Hugo Silva, Proctor, Robert, Buhler, Jared Peter, Allen, Marshall Scott
• Granted Patent: US 9,845,691 B2
• Time in Patent Office: Days
• US Class Current: 415/208.1
• CPC Class Codes: F01D 25/00 Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05B 2230/237 Brazing
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.

Claims

1. A turbine nozzle segment comprising:

an arcuate outer band segment;

an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior;

an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and

at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the at least one impingement insert mating with an opening in the impingement baffle assembly such that the at least one impingement insert is isolated from direct fluid communication with the impingement cavity.

2. The turbine nozzle segment of claim 1 wherein:

the outer band segment includes a central portion, an arcuate, radially-outwardly-extending forward rail, and an arcuate, radially-outwardly-extending aft rail; and

the forward rail, the central portion, and the aft rail all terminate at a common side face on each lateral side of the outer band segment.

3. The turbine nozzle segment of claim 2 wherein each side face includes at least one seal slot formed therein configured to receive a spline seal.

4. The turbine nozzle segment of claim 1 wherein frame includes a forward edge, an aft edge, and spaced-apart side edges, the forward edge mating with the forward rail of the outer band segment and the aft edge mating with the aft rail of the outer band segment.

5. The turbine nozzle segment of claim 3 wherein each of the side faces of the outer band segment defines spaced-apart radially inner and outer rails.

6. The turbine nozzle segment of claim 1 wherein forward and aft impingement inserts are received in the interior of the turbine vane, and mate with forward and aft openings, respectively, of the impingement baffle assembly.

7. The turbine nozzle segment of claim 1 wherein the impingement insert has an airfoil cross-sectional shape.

8. The turbine nozzle segment of claim 1 wherein the impingement baffle has a plurality of impingement holes formed therein.

9. The turbine nozzle segment of claim 1 wherein the impingement baffle assembly includes a perimeter frame and an impingement baffle extending radially inward from the frame.

10. The turbine nozzle segment of claim 3 wherein the impingement baffle assembly is brazed to the outer band.

11. The turbine nozzle segment of claim 1 wherein the impingement insert is brazed to the impingement baffle.

12. The turbine nozzle segment of claim 1 further comprising an arcuate inner band segment disposed at a radially inner end of the turbine vane.

13. A turbine nozzle assembly for a gas turbine engine, comprising:

a plurality of turbine nozzle segments arranged in an annular array, each turbine nozzle segment comprising;

an arcuate outer band segment;

an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior;

an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and

at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the at least one impingement insert mating with an opening in the impingement baffle assembly such that the at least one impingement insert is isolated from direct fluid communication with the impingement cavity; and

an annular supporting structure surrounding the turbine nozzle segments.

14. The turbine nozzle assembly of claim 13 wherein:

each outer band segment includes a central portion, an arcuate, radially-outwardly-extending forward rail, and an arcuate, radially-outwardly-extending aft rail; and

the forward rail, the central portion, and the aft rail all terminate at a common side face on each lateral side of the outer band segment.

15. The turbine nozzle assembly of claim 14 wherein each side face includes at least one seal slot formed therein configured to receive a spline seal.

16. The turbine nozzle assembly of claim 13 wherein each frame includes a forward edge, an aft edge, and spaced-apart side edges, the forward edge mating with the forward rail of the associated outer band segment and the aft edge mating with the aft rail of the associated outer band segment.

17. The turbine nozzle assembly of claim 16 wherein each of the side faces of each outer band segment defines spaced-apart radially inner and outer rails.

18. The turbine nozzle assembly of claim 13 wherein forward and aft impingement inserts are received in the interior of the turbine vane, and mate with forward and aft openings, respectively, of the impingement baffle assembly.

19. The turbine nozzle assembly of claim 13 wherein each port has a racetrack cross-sectional shape.

20. The turbine nozzle assembly of claim 13 wherein each impingement baffle has a plurality of impingement holes formed therein.

21. The turbine nozzle assembly of claim 13 wherein the impingement baffle assembly includes a perimeter frame and an impingement baffle extending radially inward from the frame.

22. The turbine nozzle assembly of claim 13 wherein the impingement baffle assembly is brazed to the outer band.

23. The turbine nozzle assembly of claim 13 wherein each port is brazed to the associated impingement baffle.

24. The turbine nozzle assembly of claim 13 further comprising an arcuate inner band segment disposed at a radially inner end of each turbine vane.