Impingement system for an airfoil

• US 10,443,397 B2
• Filed: 08/12/2016
• Issued: 10/15/2019
• Est. Priority Date: 08/12/2016
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Wiedenhoefer, James Fredric, Brzek, Brian Gene
• Primary Examiner(s): Newton, J. Todd
• Application Number:
  US15/236,045
• Publication Number:
  US 20180045056A1
• Time in Patent Office: 1,159 Days
• Field of Search: 60806
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/123 related to the pressure side of a stator vane
• CPC Class Codes: F05D 2240/124 related to the suction side of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil includes an exterior wall, a triple trailing edge pin bank, and first and second impingement systems. The exterior wall defines a first interior space. A segmenting wall divides the first interior space into a second and a first interior space. The first impingement system is disposed within the first interior space and the second impingement system is disposed within the first interior space. First impingement system includes impingement holes with a first impingement hole density. Second impingement system includes impingement holes with a second impingement hole density. The impingement systems also include dividing walls extending from a first and second interior wall to the exterior wall. The interior walls, exterior wall, and dividing walls define a first and second zone. The first and second impingement hole density is configured to separately meter flow to the first and second zones.

Claims

1. An airfoil comprising:

an exterior wall comprising an inner surface, an outer surface, and a plurality of exterior wall regions, said exterior wall defining a first interior space, said exterior wall further comprising;

a pressure sidewall; and

a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and a trailing edge opposite said leading edge;

a root portion;

a tip portion opposite said root portion;

a triple trailing edge pin bank disposed within said first interior space;

a first impingement system disposed within said first interior space and a second impingement system disposed within said first interior space, said first and second impingement systems configured to channel a coolant stream to said exterior wall, said first impingement system comprising a first interior wall portion substantially parallel to said exterior wall and defining a second interior space, said first interior wall portion further defines a plurality of first impingement holes configured to channel a flow of coolant from said second interior space to said first interior space, said first interior wall portion having a first impingement hole density, said second impingement system comprising a second interior wall portion substantially parallel to said exterior wall and defining a third interior space, said second interior wall portion further defines a plurality of second impingement holes configured to channel a flow of coolant from said third interior space to said first interior space, said second interior wall portion having a second impingement hole density; and

a plurality of dividing walls comprising a first dividing wall and a second dividing wall extending from said first and second interior wall portions to said exterior wall, said first and second interior wall portions, said exterior wall, and said plurality of dividing walls define a first zone and a second zone, said first zone and said second zone coupled in flow communication, wherein said first and second impingement hole densities are each configured to separately meter flow to said first and second zones, wherein said exterior wall further defines a plurality of film holes configured to separately meter flow to said first and second zones by channeling the flow of coolant from said first interior space.

2. The airfoil in accordance with claim 1, wherein said first and second zones configured to channel said flow of coolant to said triple trailing edge pin bank, said flow of coolant within said triple trailing edge pin bank having a pressure drop, said pressure drop configured to separately meter flow to said first and second zones.

3. The airfoil in accordance with claim 2, wherein said first and second interior wall portions, said exterior wall, and said plurality of dividing walls further define a third zone, said first dividing wall separating said first zone from said third zone and said second dividing wall separating said second zone from said third zone, said first, second, and third zones having a compartmentalized arrangement, said compartmentalized arrangement configured to separately meter flow to said first, second, and third zones.

4. The airfoil in accordance with claim 3, wherein said plurality of impingement holes and said plurality of film holes are arranged to channel the flow of coolant within said first zone, said second zone, and said third zone in a bidirectional crossflow pattern.

5. The airfoil in accordance with claim 1, wherein said triple trailing edge pin bank comprises:

a first plurality of projections coupled to said suction sidewall adjacent said trailing edge and extending from said suction sidewall towards said pressure sidewall;

a second plurality of projections coupled to said pressure sidewall adjacent said trailing edge and extending from said pressure sidewall towards said suction sidewall; and

a divider coupled to said first plurality of projections and said second plurality of projections and extending within a space defined between said first plurality of projections and said second plurality of projections such that a first cooling channel is defined adjacent said suction sidewall and a second cooling channel is defined adjacent said pressure sidewall, said first cooling channel and said second cooling channel configured to receive at least one coolant stream, said first plurality of projections configured to meter the at least one coolant stream through said first cooling channel and said second plurality of projections configured to meter the at least one coolant stream through said second cooling channel.

6. A system for removing heat from an airfoil, the airfoil including a triple trailing edge pin bank and an exterior wall including an inner surface, an outer surface, and a plurality of exterior wall regions, the exterior wall defining a first interior space, the exterior wall comprising a pressure sidewall, a suction sidewall coupled to the pressure sidewall, wherein the suction sidewall and the pressure sidewall define a leading edge and a trailing edge opposite the leading edge, the airfoil further including a root portion and a tip portion opposite the root portion, said system comprising:

a first impingement system disposed within said first interior space and a second impingement system disposed within said first interior space, said first and second impingement systems configured to channel a coolant stream to said exterior wall, said first impingement system comprising a first interior wall portion substantially parallel to said exterior wall and defining a second interior space, said first interior wall portion further defines a plurality of first impingement holes configured to channel a flow of coolant from said second interior space to said first interior space, said first interior wall portion having a first impingement hole density, said second impingement system comprising a second interior wall portion substantially parallel to said exterior wall and defining a third interior space, said second interior wall portion further defines a plurality of second impingement holes configured to channel a flow of coolant from said third interior space to said first interior space, said second interior wall portion having a second impingement hole density; and

a plurality of dividing walls comprising a first dividing wall and a second dividing wall extending from said first and second interior walls to said exterior wall, said first and second interior wall portions, said exterior wall, and said plurality of dividing walls define a first zone and a second zone, said first zone and said second zone coupled in flow communication, wherein said first and second impingement hole densities are each configured to separately meter flow to said first and second zones, wherein the exterior wall further defines a plurality of film holes configured to separately meter flow to said first and second zones by channeling the flow of coolant from said first interior space.

7. The system for removing heat from an airfoil in accordance with claim 6, wherein said first and second zones configured to channel said flow of coolant to said triple trailing edge pin bank, said flow of coolant within said triple trailing edge pin bank having a pressure drop, said pressure drop configured to separately meter flow to said first and second zones.

8. The system for removing heat from an airfoil in accordance with claim 7, wherein said first and second interior wall portions, the exterior wall, and said plurality of dividing walls further define a third zone, said first dividing wall separating said first zone from said third zone and said second dividing wall separating said second zone from said third zone, said first, second, and third zones having a compartmentalized arrangement, said compartmentalized arrangement configured to separately meter flow to said first, second, and third zones.

9. The system for removing heat from an airfoil in accordance with claim 8, wherein said plurality of impingement holes and said plurality of film holes are arranged to channel the flow of coolant within said first zone, said second zone, and said third zone in a bidirectional crossflow pattern.

10. A gas turbine system, said gas turbine system comprising:

a compressor section;

a combustion system coupled in flow communication with said compressor section; and

a turbine section coupled in flow communication with said combustion system, wherein said turbine section comprises;

an airfoil comprising;

an exterior wall comprising an inner surface, an outer surface, and a plurality of exterior wall regions, said exterior wall defining a first interior space, said exterior wall further comprising;

a pressure sidewall; and

a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and a trailing edge opposite said leading edge;

a root portion;

a tip portion opposite said root portion;

a triple trailing edge pin bank disposed within said first interior space;

a first impingement system disposed within said first interior space and a second impingement system disposed within said first interior space, said first and second impingement systems configured to channel a coolant stream to said exterior wall, said first impingement system comprising a first interior wall portion substantially parallel to said exterior wall and defining a second interior space, said first interior wall portion further defines a plurality of first impingement holes configured to channel a flow of coolant from said second interior space to said first interior space, said first interior wall portion having a first impingement hole density, said second impingement system comprising a second interior wall portion substantially parallel to said exterior wall and defining a third interior space, said second interior wall portion further defines a plurality of second impingement holes configured to channel a flow of coolant from said third interior space to said first interior space, said second interior wall having a second impingement hole density; and

a plurality of dividing walls comprising a first dividing wall and a second dividing wall extending from said first and second interior wall portions to said exterior wall, said first and second interior wall portions, said exterior wall, and said plurality of dividing walls define a first zone and a second zone, said first zone and said second zone coupled in flow communication, wherein said first and second impingement hole densities are each configured to separately meter flow to said first and second zones , wherein said exterior wall further defines a plurality of film holes configured to separately meter flow to said first and second zones by channeling the flow of coolant from said first interior space.

11. The gas turbine in accordance with claim 10, wherein said first and second zones configured to channel said flow of coolant to said triple trailing edge pin bank, said flow of coolant within said triple trailing edge pin bank having a pressure drop, said pressure drop configured to separately meter flow to said first and second zones.

12. The gas turbine in accordance with claim 11, wherein said first and second interior walls, said exterior wall, and said plurality of dividing walls further define a third zone, said first dividing wall separating said first zone from said third zone and said second dividing wall separating said second zone from said third zone, said first, second, and third zones having a compartmentalized arrangement, said compartmentalized arrangement configured to separately meter flow to said first, second, and third zones.

13. The gas turbine in accordance with claim 12, wherein said plurality of impingement holes and said plurality of film holes are arranged to channel the flow of coolant within said first zone, said second zone, and said third zone in a bidirectional crossflow pattern.

14. The gas turbine in accordance with claim 10, wherein said triple trailing edge pin bank comprises:

a first plurality of projections coupled to said suction sidewall adjacent said trailing edge and extending from said suction sidewall towards said pressure sidewall;

a second plurality of projections coupled to said pressure sidewall adjacent said trailing edge and extending from said pressure sidewall towards said suction sidewall; and

a divider coupled to said first plurality of projections and said second plurality of projections and extending within a space defined between said first plurality of projections and said second plurality of projections such that a first cooling channel is defined adjacent said suction sidewall and a second cooling channel is defined adjacent said pressure sidewall, said first cooling channel and said second cooling channel configured to receive at least one coolant stream, said first plurality of projections configured to meter the at least one coolant stream through said first cooling channel and said second plurality of projections configured to meter the at least one coolant stream through said second cooling channel.