COOLING SYSTEM AND METHOD FOR TURBINE SYSTEM

• US 20130298564A1
• Filed: 05/14/2012
• Published: 11/14/2013
• Est. Priority Date: 05/14/2012
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Agarwal, Krishna Kant
• Application Number:
  US13/470,556
• Publication Number:
  US 20130298564A1
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube

Abstract

A cooling system and a method for cooling a liner in a turbine system are disclosed. The cooling system includes a liner defining a temperature boundary between a hot side and a cold side. The liner includes a hot side surface and a cold side surface and defines a hole extending between the hot side surface and the cold side surface. The hole defines a peripheral edge. The cooling system further includes an insert. The insert includes a tube extending through the hole, the tube including an outer surface. The outer surface and the peripheral edge define a generally continuous peripheral gap therebetween. The insert further includes a plate connected to the tube and disposed in the hot side. The plate extends outwardly from the tube such that working fluid flowing through the gap is redirected by the plate to form a film proximate the hot side surface.

Claims

1. A cooling system for a turbine system, comprising:

a liner defining a temperature boundary between a hot side and a cold side, the liner comprising a hot side surface and a cold side surface and defining a hole extending between the hot side surface and the cold side surface, the hole defining a peripheral edge; and

an insert comprising;

a tube extending through the hole, the tube comprising an outer surface, the outer surface and the peripheral edge defining a generally continuous peripheral gap therebetween; and

a plate connected to the tube and disposed in the hot side, the plate extending outwardly from the tube such that working fluid flowing through the gap is redirected by the plate to form a film proximate the hot side surface.

2. The cooling system of claim 1, wherein the tube is a generally cylindrical tube, and wherein the plate extends generally radially outward from the outer surface of the tube.

3. The cooling system of claim 1, wherein the plate is a first plate, further comprising a second plate connected to the tube and disposed in the cold side, the second plate extending generally outwardly from the tube such that working fluid flows between the second plate and the cold side surface into the gap.

4. The cooling system of claim 3, further comprising a plurality of studs each extending between the second plate and the cold side surface.

5. The cooling system of claim 1, further comprising a plurality of ribs disposed in the cold side, each of the plurality of ribs connecting the tube and the cold side surface.

6. The cooling system of claim 1, further comprising a plurality of spacers each extending through the gap, each of the plurality of spacers positioning the tube within the hole.

7. The cooling system of claim 6, wherein each of the plurality of spacers is connected to the outer surface of the tube.

8. The cooling system of claim 6, wherein each of the plurality of spacers is connected to the outer surface of the tube and to the peripheral edge, and wherein each of the plurality of spacers further defines a hole therethrough.

9. The cooling system of claim 1, wherein the liner is a combustor liner and the hole is a dilution hole.

10. A combustor for a turbine system, the combustor comprising:

a combustor liner defining a temperature boundary between a combustion zone and a flow passage, the liner comprising a hot side surface and a cold side surface and defining a dilution hole extending between the hot side surface and the cold side surface, the dilution hole defining a peripheral edge; and

an insert comprising;

a tube extending through the dilution hole, the tube comprising an outer surface, the outer surface and the peripheral edge defining a generally continuous peripheral gap therebetween; and

a plate connected to the tube and disposed in the combustion zone, the plate extending outwardly from the tube such that working fluid flowing through the gap is redirected by the plate to form a film proximate the hot side surface.

11. The combustor of claim 10, wherein the tube is a generally cylindrical tube, and wherein the plate extends generally radially outward from the outer surface of the tube.

12. The combustor of claim 10, wherein the plate is a first plate, further comprising a second plate connected to the tube and disposed in the flow passage, the second plate extending outwardly from the tube such that working fluid flows between the second plate and the cold side surface into the gap.

13. The combustor of claim 12, further comprising a plurality of studs each extending between the second plate and the cold side surface.

14. The combustor of claim 10, further comprising a plurality of ribs disposed in the flow passage, each of the plurality of ribs connecting the tube and the cold side surface.

15. The combustor of claim 10, further comprising a plurality of spacers each extending through the gap, each of the plurality of spacers positioning the tube within the dilution hole.

16. The combustor of claim 15, wherein each of the plurality of spacers is connected to the outer surface of the tube.

17. The combustor of claim 15, wherein each of the plurality of spacers is connected to the outer surface of the tube and to the peripheral edge, and wherein each of the plurality of spacers further defines a hole therethrough.

18. The combustor of claim 10, wherein the turbine system is a gas turbine system.

19. A method for cooling a liner in a turbine system, the method comprising:

flowing a working fluid through a generally continuous peripheral gap defined in the liner between an outer surface of a tube disposed in a hole and a peripheral edge of the hole;

redirecting the working fluid flowed through the gap to form a film proximate a hot side surface of the liner.

20. The method of claim 19, wherein the working fluid is redirected by a plate connected to the tube and extending outwardly from the tube.