Gas turbine engine trailing edge ejection holes

Patent metadata

Field	Value
Publication number	US-10563518-B2
Application number	US-201615043933-A
Country	US
Kind code	B2
Filing date	Feb 15, 2016
Priority date	Feb 15, 2016
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

An apparatus and method for an airfoil for a gas turbine engine includes a trailing edge cooling circuit utilizing a plurality of trailing edge ejection holes. The ejection holes can include a circumferentially radiused inlet, a converging section, a metering section, and a diverging section to improve airfoil cooling as well as castability.

First claim

What is claimed is:

1. An airfoil for a turbine engine comprising:
an outer wall defining an interior including a pressure sidewall and a suction sidewall extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction; and
a trailing edge cooling circuit formed within the interior comprising:
a trailing edge plenum extending in the span-wise direction and including a set of elongated turbulators, the trailing edge plenum transitioning to a flag passage at a tip turn, with the flag passage extending in the chord-wise direction;
an exhaust passage downstream of the trailing edge plenum and including a plurality of pin holes forming a pin bank arranged in the exhaust passage;
a set of impingement holes in span-wise arrangement extending between, and fluidly coupling, the trailing edge plenum and the exhaust passage, wherein fluid from the trailing edge plenum is directed toward the pin bank via the set of impingement holes;
a set of trailing edge ejection holes in fluid communication with the exhaust passage and adjacent the trailing edge in span-wise arrangement, with each trailing edge ejection hole of the set of trailing edge ejection holes including a radiused inlet section, a converging section, a metering section having a constant cross-section extending in the chord-wise direction, and a diverging section;
a dividing wall physically separating the flag passage from the exhaust passage, and at least partially forming one trailing edge ejection hole of the set of trailing edge ejection holes; and
a tip cooling passage arranged at the tip, radially outward of the trailing edge plenum, tip turn, and flag passage, with the tip cooling passage fluidly coupled to the trailing edge plenum.

2. The airfoil of claim 1 wherein the converging section includes a decreasing cross-sectional area to accelerate a flow of air into each trailing edge ejection hole of the set of trailing edge ejection holes.

3. The airfoil of claim 2 wherein the diverging section includes an increasing cross-sectional area to decelerate the flow of air exiting each trailing edge ejection hole of the set of trailing edge ejection holes.

4. The airfoil of claim 3 wherein the diverging section defines an expansion angle being 7 degrees or less.

5. The airfoil of claim 1 wherein a centerline of each trailing edge ejection hole of the set of trailing edge ejection holes is parallel to one of the pressure sidewall or the suction sidewall.

6. The airfoil of claim 1 wherein a centerline of each trailing edge ejection hole of the set of trailing edge ejection holes equally bisects the airfoil.

7. The airfoil of claim 1 wherein the metering section has a length and a diameter defining a length to diameter ratio of at least 1.

8. The airfoil of claim 7 wherein the length to diameter ratio is 2.

9. The airfoil of claim 1 wherein the airfoil is one of a blade or a vane.

10. The airfoil of claim 1 further comprising a plurality of turbulators disposed in the set of trailing edge ejection holes.

11. The airfoil of claim 1 wherein the tip cooling passage being fluidly coupled to the trailing edge plenum is provided by a tip duct.

12. The airfoil of claim 1 wherein at least some of the set of trailing edge ejection holes are provided in the flag passage exhausting to the trailing edge.

13. The airfoil of claim 1 wherein the dividing wall terminates prior to the trailing edge.

14. An airfoil for a turbine engine comprising:
an outer wall defining an interior including a pressure sidewall and a suction sidewall extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction; and
a trailing edge cooling circuit formed within the interior comprising:
a trailing edge plenum extending in the span-wise direction and transitioning to a flag passage at a tip turn, with the flag passage extending in the chord-wise direction;
an exhaust passage downstream of, and fluidly coupled to, the trailing edge plenum;
a set of impingement holes in span-wise arrangement extending between, and fluidly coupling, the trailing edge plenum and the exhaust passage;
a tip cooling passage located radially outward of the trailing edge plenum, the tip turn, and the flag passage, and fluidly coupled to the flag passage;
a set of trailing edge ejection holes in fluid communication with the exhaust passage and adjacent the trailing edge in span-wise arrangement;
a first dividing wall at least partially defining the flag passage and the exhaust passage, and physically separating the exhaust passage from the flag passage and at least partially forming one trailing edge ejection hole of the set of trailing edge ejection holes; and
a second dividing wall at least partially defining the tip cooling passage and the flag passage, and physically separating the tip cooling passage from the flag passage.

15. The airfoil of claim 14 wherein at least one of the first or second dividing walls terminates upstream of the trailing edge.

16. The airfoil of claim 14 further comprising a tip duct extending through the second dividing wall to provide the fluid coupling between the flag passage and the tip cooling passage.

17. The airfoil of claim 16 wherein the set of trailing edge ejection holes exhaust to the trailing edge.

18. The airfoil of claim 17 wherein at least some of the trailing edge ejection holes in the set are provided in the flag passage.

19. The airfoil of claim 17 wherein each of the trailing edge ejection holes in the set comprises a radiused inlet section, a converging section, a metering section, and a diverging section in axial flow arrangement.

20. The airfoil of claim 19 wherein the metering section includes a constant cross-section extending in the chord-wise direction.

21. The airfoil of claim 20 wherein the converging section includes a decreasing cross-sectional area to accelerate a flow of air into each trailing edge ejection hole of the set of trailing edge ejection holes.

22. The airfoil of claim 21 wherein the diverging section includes an increasing cross-sectional area to decelerate the flow of air exiting each trailing edge ejection hole of the set of trailing edge ejection holes.

23. The airfoil of claim 22 wherein the diverging section defines an expansion angle being 7 degrees or less.

24. The airfoil of claim 19 wherein a centerline of each trailing edge ejection hole of the set of trailing edge ejection holes is parallel to one of the pressure sidewall or the suction sidewall.

25. The airfoil of claim 19 wherein a centerline of each trailing edge ejection hole of the set of trailing edge ejection holes equally bisects the airfoil.

26. The airfoil of claim 19 wherein the metering section has a length and a diameter defining a length to diameter ratio of at least 1.

27. The airfoil of claim 26 wherein the length to diameter ratio is 2.

28. The airfoil of claim 17 further comprising a plurality of turbulators disposed in the set of trailing edge ejection holes.

29. The airfoil of claim 14 further comprising a plurality of pin holes forming a pin bank arranged in the exhaust passage upstream of the trailing edge.

Assignees

• Gen Electric

Inventors

• Konitzer Douglas Gerard
• Krumanaker Matthew Lee
• Dooley Weston Nolan
• Deines James Herbert

Classifications

• F05D2250/712

  concave · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · 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