Turbine vane cluster including enhanced vane cooling

Patent metadata

Field	Value
Publication number	US-10641102-B2
Application number	US-201715790505-A
Country	US
Kind code	B2
Filing date	Oct 23, 2017
Priority date	Sep 1, 2017
Publication date	May 5, 2020
Grant date	May 5, 2020

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.

First claim

The invention claimed is:

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.

Assignees

• United Technologies Corp

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

Classifications

• B23P15/02

  turbine or like blades from one piece · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2230/12

  by spark erosion methods · CPC title

• F01D9/065

  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 title