Tip leakage flow directionality control

Patent metadata

Field	Value
Publication number	US-9777582-B2
Application number	US-201314143115-A
Country	US
Kind code	B2
Filing date	Dec 30, 2013
Priority date	Jul 3, 2012
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane.

First claim

What is claimed is:

1. An airfoil, comprising:
a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge;
a tip wall extending chordwise from said leading edge to said trailing edge and joining respective outer spanwise ends of said suction and pressure sidewalls;
a tip leakage control vane formed with an outer surface of said tip wall;
a winglet formed at a junction between said suction sidewall and said tip leakage control vane; and
wherein said winglet is localized at said tip leakage control vane.

2. The airfoil as recited in claim 1 , wherein said tip leakage control vane is curved.

3. The airfoil as recited in claim 1 , wherein said winglet spans a distance between said leading edge and said trailing edge.

4. The airfoil as recited in claim 1 , comprising a plurality of tip leakage control vanes distributed across a chordwise portion of said tip wall between said leading edge and said trailing edge.

5. The airfoil as recited in claim 4 , wherein each of said plurality of tip leakage control vanes includes a winglet.

6. The airfoil as recited in claim 5 , wherein each winglet is a discrete portion of said tip wall that extends from one of said plurality of tip leakage control vanes.

7. The airfoil as recited in claim 4 , comprising a corresponding tip leakage control channel defined at least in part by adjacent ones of said plurality of tip leakage control vanes.

8. The airfoil as recited in claim 1 , wherein said tip leakage control vane includes a first control channel vane sidewall and a second control channel vane sidewall, and a control channel floor of a corresponding tip leakage control channel extends between said first control channel vane sidewall and said second control channel vane sidewall.

9. The airfoil as recited in claim 8 , comprising radiused walls that connect said first control channel vane sidewall and said second control channel vane sidewall to said control channel floor.

10. The airfoil as recited in claim 1 , comprising an airfoil sidewall microcircuit formed in either said suction sidewall or said pressure sidewall.

11. The airfoil as recited in claim 10 , wherein said airfoil sidewall microcircuit feeds into an inlet of a tip leakage control channel that is recessed into said tip wall and disposed adjacent to said tip leakage control vane.

12. The airfoil as recited in claim 10 , wherein said airfoil sidewall microcircuit feeds into a tip shelf cooling aperture.

13. A gas turbine engine, comprising:
an airfoil that includes:
a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge;
a tip wall extending chordwise from said leading edge to said trailing edge and joining respective outer spanwise ends of said suction and pressure sidewalls;
a tip leakage control vane formed with an outer surface of said tip wall; and
a winglet formed at a junction between said suction sidewall and said tip leakage control vane, wherein said winglet is localized at said tip leakage control vane.

14. The gas turbine engine as recited in claim 13 , wherein said tip wall includes a tip outer surface having a first surface and an angled surface.

15. The gas turbine engine as recited in claim 14 , wherein said first surface extends from a tip shelf to a tip rib suction side of said tip wall.

16. The gas turbine engine as recited in claim 14 , wherein said angled surface extends radially inwardly from said first surface into said tip leakage control channel.

17. The gas turbine engine as recited in claim 13 , comprising a tip leakage control channel recessed into said tip wall.

18. The gas turbine engine as recited in claim 17 , wherein said tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall, and at least one radiused wall connects said control channel floor to at least one of said first control channel vane sidewall and said second control channel vane sidewall.

19. A method for reducing airfoil tip leakage losses, comprising:
capturing a leakage flow in a tip leakage control channel recessed into an outer surface of a tip wall of an airfoil;
directing the leakage flow tangentially against a tip leakage control vane to recover work from the captured leakage flow;
ejecting the leakage flow out of the tip leakage control channel at a suction sidewall of the airfoil; and
reducing inducement of a vortex that results from the leakage flow joining a suction side gas flow near the suction sidewall with a winglet, wherein the winglet is formed at a junction between the suction sidewall and the tip leakage control vane and is localized at the tip leakage control vane.

20. The method as recited in claim 19 , comprising redirecting the leakage flow toward an airfoil trailing edge through a curved portion of the tip leakage control channel.

21. The method as recited in claim 19 , wherein ejecting the leakage flow includes expelling the leakage flow through an outlet of the tip leakage control channel such that the leakage flow joins a suction gas flow at a downstream location from an inlet of the tip leakage control channel.

Assignees

• Zelesky Mark F
• Aggarwala Andrew S
• United Technologies Corp

Inventors

• Zelesky Mark F
• Aggarwala Andrew S

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2240/126

  Baffles or ribs · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title