Two stage serial impingement cooling for isogrid structures

• US 8,826,668 B2
• Filed: 08/02/2011
• Issued: 09/09/2014
• Est. Priority Date: 08/02/2011
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Lee, Ching-Pang, Morrison, Jay A.
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): Mantyla, Michael B
• Application Number:
  US13/195,947
• Publication Number:
  US 20130031914A1
• Time in Patent Office: 1,134 Days
• Field of Search: 607/52, 607/53, 607/54, 607/55, 607/56, 607/57, 607/58, 607/59, 607/60, 602/62, 607/82, 607/85, 607/98, 608/06, 415/114, 415/115, 415/116, 415/117, 415/175, 415/178, 416/96.R, 416/96.A, 416/97.R, 165/908
• US Class Current: 60/755
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• 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: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F23R 2900/00017 Assembling combustion chamber liners or subparts
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y10S 165/908 Fluid jets

Abstract

A system for cooling a wall (24) of a component having an outer surface with raised ribs (12) defining a structural pocket (10), including: an inner wall (26) within the structural pocket and separating the wall outer surface within the pocket into a first region (28) outside of the inner wall and a second region (40) enclosed by the inner wall; a plate (14) disposed atop the raised ribs and enclosing the structural pocket, the plate having a plate impingement hole (16) to direct cooling air onto an impingement cooled area (38) of the first region; a cap having a skirt (50) in contact with the inner wall, the cap having a cap impingement hole (20) configured to direct the cooling air onto an impingement cooled area (44) of the second region, and; a film cooling hole (22) formed through the wall in the second region.

Claims

1. A system for cooling a wall of a gas turbine engine component heated by a flow of a hot gas across an inner surface of the wall, the wall having an outer surface comprising raised ribs defining a plurality of structural pockets, the system comprising:

an inner wall within each structural pocket, the inner wall extending from the wall outer surface within a respective structural pocket and separating the wall outer surface within the respective structural pocket into a first region outside of the inner wall and a second region enclosed by the inner wall, wherein the inner wall is spaced apart from the raised ribs, and an outer surface of the inner wall in contact with the first region and enclosing an inner surface of the inner wall;

a plate disposed atop the raised ribs and enclosing the plurality of structural pockets, the plate comprising a plurality of plate impingement holes, each configured to direct cooling air from outside each respective structural pocket onto an impingement cooled area of the first region within each respective structural pocket;

a cap within each structural pocket, comprising a skirt that extends toward the wall and that is in contact with the outer surface of the inner wall within each respective structural pocket, wherein the skirt encloses the inner wall and configured to secure the cap in position over the respective second region, the cap comprising a cap impingement hole configured to direct the cooling air that has impingement cooled the respective first region onto an impingement cooled area of the respective second region, and;

a film cooling hole formed through the wall in the second region for removing the cooling air from the respective structural pocket.

2. The system of claim 1, wherein at least one cap forms a seal with a respective inner wall.

3. The system of claim 1, wherein a geometric feature of at least one skirt engages a geometric feature of the respective inner wall to hold the respective cap in position.

4. The system of claim 1, wherein resilience of at least one cap urges the respective skirt against the outer surface of the respective inner wall to hold the at least one cap in position.

5. The system of claim 1, wherein at least one skirt comprises barbs that engage the respective inner wall.

6. The system of claim 1, wherein with respect to a direction of flow of the hot gas, at least one film cooling hole is offset laterally from a film cooling hole of an adjacent structural pocket disposed upstream or downstream.

7. The system of claim 1, wherein with respect to a direction of flow of the hot gas, at least one film cooling hole is disposed upstream of an area of the respective first region remote from the impingement cooled area of the respective first region.

8. The system of claim 1, wherein with respect to a direction of flow of the hot gas, at least one film cooling hole is offset laterally from the impingement cooled area of the respective first region.

9. The system of claim 1, wherein either at least one cap or at least one plate comprises a stop feature configured to prevent the respective cap from lifting off the respective inner wall.

10. The system of claim 1, wherein at least one plate impingement hole is disposed on a portion of the respective plate lowered toward the respective first region relative to another portion of the respective plate.

11. The system of claim 1, further comprising a seal between at least one cap and the respective inner wall configured such that differential thermal expansion caused by heating of the component from ambient to an operational temperature tightens the seal.

12. The system of claim 1, wherein at least one skirt is rounded where the at least one skirt contacts the respective inner wall and thus retains contact if a span of the respective cap deflects due to a pressure difference across the span.

13. The system of claim 1, wherein in at least one structural pocket a ratio of cooling holes per unit of surface area is lower in the first region than in the second region.

14. A system for cooling a wall of a gas turbine engine component, the wall being exposed during operation of the gas turbine engine to a relatively higher pressure cooling air on a first side and to a relatively lower pressure hot combustion gas on an opposed second side, the system comprising:

a transition duct comprising the wall;

structural ribs extending from the first side of the wall and defining a structural pocket and plural adjacent structural pockets;

an inner wall extending from the first side of the wall within the structural pocket and separating the structural pocket into a first volume outside of the inner wall and a second volume enclosed by the inner wall, the inner wall extending from the first side to a height lower than a height of the structural ribs and spaced apart from the raised ribs, and an outer surface of the inner wall in facing the first volume and enclosing an inner surface of the inner wall;

a plate disposed atop the structural ribs and enclosing the structural pocket and the plural adjacent structural pockets;

a cap enclosing the second volume and comprising a skirt that extends toward the wall and that is in contact with the outer surface of the inner wall;

a series flow path for cooling air from the relatively higher pressure first side to the relatively lower pressure second side comprising a plate impingement hole, the first volume, a cap impingement hole, the second volume, and a film cooling hole through the wall where the wall defines part of the second volume;

the plate impingement hole and first volume effective to accomplish a first pressure drop in the cooling air and a first heat transfer from the wall to the cooling air;

the cap impingement hole and the second volume effective to accomplish a second pressure drop in the cooling air and a second heat transfer from the wall to the cooling air;

the film cooling hole effective to accomplish a third pressure drop in the cooling air and a third heat transfer from the wall to the cooling air and to create a film cooling layer along the second side.

15. The system of claim 14, wherein with respect to a direction of flow of the hot combustion gas, the film cooling hole is offset laterally from the plate impingement hole and the cap impingement hole.

16. A system for cooling a hot wall of a gas turbine engine component comprising an outer side comprising continuous raised ribs defining discrete structural pockets, comprising:

a plurality of discrete structural pockets, each of the discrete structural pockets comprising an inner pocket that is defined by a continuous inner wall, the continuous inner wall comprising an inner surface that defines the inner pocket, and an outer surface that faces away from the inner pocket and encloses the inner surface, wherein the continuous inner wall is spaced apart from the continuous raised ribs;

a plate disposed atop the continuous raised ribs, thereby enclosing the plurality of discrete structural pockets, the plate comprising a plate impingement hole for each of the plurality of discrete structural pockets that is configured to direct cooling air toward a respective structural pocket surface outside the respective inner pocket;

a discrete cap disposed on each continuous inner wall to enclose the inner pocket, each cap comprising a skirt that extends toward the hot wall and that is in contact with the outer surface of the continuous inner wall, and a cap impingement hole configured to direct respective cooling air toward a respective pocket surface inside the respective inner pocket, wherein abutting surfaces of the cap and the respective continuous inner wall are free to thermally expand and contract with respect to each other;

a film cooling hole in each discrete structural pocket that is configured to deliver the respective cooling air from respective inner pocket through an inner side of the hot wall.

17. The system of claim 16, wherein the abutting surfaces of at least one cap and a respective continuous inner wall form a seal effective to block cooling air from flowing there between.

18. The system of claim 16, wherein at least one cap comprises a skirt that forms a seal with the outer surface of the respective inner wall.