Turbine vane cluster including enhanced vane cooling

• US 10,641,102 B2
• Filed: 10/23/2017
• Issued: 05/05/2020
• Est. Priority Date: 09/01/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: McMahon, Shawn M., Whitfield, Christopher, Anderson, Kristopher K., Moran, Jason B., Bartling, Brett Alan, Perron, Christopher, Aniello, Justin M., Tanner, Stephanie, Mongillo, Jr., Dominic J.
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): Gillenwaters, Jackson N
• Application Number:
  US15/790,505
• Publication Number:
  US 20190071979A1
• Time in Patent Office: 925 Days
• CPC Class Codes: B23H 1/00 Electrical discharge machining, i.e. removing metal with a series of rapidly recurring electrical discharges between an electrode and a workpiece in the presence of a fluid dielectric
• CPC Class Codes: B23P 15/02 turbine or like blades from one piece
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/12 by spark erosion methods
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/124 related to the suction side of a stator vane
• CPC Class Codes: F05D 2250/141 circular
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

Claims

1. A vane cluster for a gas turbine engine comprising:

an outer diameter platform;

an inner diameter platform;

a plurality of vanes spanning from the outer diameter platform to the inner diameter platform;

at least one inbound region defined between a first vane of said plurality of vanes and a second vane of said plurality of vanes, the first vane including a suction side facing the inbound region;

each of said vanes including a leading edge core passage and a trailing edge core passage; and

no less than six and no more than ten electrical discharge machined (EDM) holes disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane, each of the EDM holes connecting a leading edge core passage of the vane to an exterior surface of the vane.

2. The vane cluster of claim 1, wherein each EDM hole is disposed on the leading edge of the first vane.

3. The vane cluster of claim 1, wherein each EDM hole includes a primary passage portion and a diffuser portion.

4. The vane cluster of claim 3, wherein each of the primary passage portions has a diameter of 0.015 inches (0.381 mm).

5. The vane cluster of claim 3, wherein each of the primary passage portions connects to the leading edge core passage of the first vane, and each of the diffuser portions connects to the leading edge of the first vane.

6. The vane cluster of claim 3, wherein each of the diffuser portions includes a gradual increase in diameter from a connection to the corresponding primary passage portion to an exit at the leading edge of the first vane.

7. The vane cluster of claim 3, wherein each of the diffuser portions is connected to the corresponding primary passage portion via an opening and wherein the diffuser portions are offset from the primary portions at the corresponding opening.

8. The vane cluster of claim 1, wherein the no less than six and no more than ten EDM holes includes eight holes.

9. The vane cluster of claim 1, wherein each of the EDM holes is a 10/10/10 hole.

10. The vane cluster of claim 1, wherein the plurality of vanes consists of the first vane and the second vane.

11. A gas turbine engine comprising:

a compressor section;

a combustor section fluidly connected to the compressor section;

a turbine section fluidly connected to the combustor section, the turbine section include a plurality of stages, at least one of said stages including a vane ring comprising multiple circumferentially adjacent vane clusters, wherein each of the vane clusters comprises

an outer diameter platform;

an inner diameter platform;

a plurality of vanes spanning from the outer diameter platform to the inner diameter platform;

at least one inbound region defined between a first vane of said plurality of vanes and a second vane of said plurality of vanes, the first vane including a suction side facing the inbound region;

each of said vanes including a leading edge core passage and a trailing edge core passage; and

no less than six and no more than ten electrical discharge machined (EDM) holes disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane, each of the EDM holes connecting a leading edge core passage of the vane to an exterior surface of the vane.

12. The gas turbine engine of claim 11, wherein each EDM hole is disposed in a visually obstructed region of the first vane.

13. The gas turbine engine of claim 11, wherein each EDM hole includes a primary passage portion and a diffuser portion.

14. The gas turbine engine of claim 13, wherein each of the primary passages has a diameter of 0.015 inches (0.381 mm).

15. The gas turbine engine of claim 13, wherein each of the primary passage portions connects to the leading edge core passage of the first vane, and each of the diffuser portions connects to a visually obstructed region of the first vane.

16. The gas turbine engine of claim 13, wherein each of the diffuser portions includes a gradual increase in diameter from a connection to the corresponding primary passage portion to an exit at a visually obstructed region of the first vane.

17. The gas turbine engine of claim 13, wherein each of the diffuser portions is connected to the corresponding primary passage portion via an opening and wherein the diffuser portions are offset from the primary portions at the corresponding opening.

18. The gas turbine engine of claim 11, wherein the no less than six and no more than ten EDM holes includes eight holes.

19. The gas turbine engine of claim 11, wherein the plurality of vanes consists of the first vane and the second vane.

20. The gas turbine engine of claim 11, wherein each of the EDM holes is a 10/10/10 hole.