Tip leakage flow directionality control

Patent metadata

Field	Value
Publication number	US-9260972-B2
Application number	US-201213540752-A
Country	US
Kind code	B2
Filing date	Jul 3, 2012
Priority date	Jul 3, 2012
Publication date	Feb 16, 2016
Grant date	Feb 16, 2016

Abstract

A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.

First claim

The invention claimed is:

1. A turbine 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 the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls; and
a plurality of tip leakage control channels distributed across at least a chordwise portion of the tip wall between the airfoil leading edge and the airfoil trailing edge, each channel recessed into an outer surface of the tip wall, an inlet of each channel beginning proximate a junction of the airfoil pressure sidewall and the tip wall, an outlet of each channel terminating at a recessed portion of a junction of the tip wall and the suction sidewall, and a portion of each channel curved toward the trailing edge from the inlet to the outlet.

2. The airfoil of claim 1 , wherein each channel inlet forms a channel entrance interior angle α 1 relative to a downstream side of the pressure sidewall, and each channel outlet forms a channel exit interior angle α 2 relative to a downstream side of the suction sidewall, angle α 2 being less than or equal to α 1 .

3. The airfoil of claim 2 , wherein the channel entrance angle α 1 is between 80° and 95°.

4. The airfoil of claim 3 , wherein the channel exit angle α 2 is less than 90°.

5. The airfoil of claim 1 , wherein a corresponding plurality of tip leakage control vanes are integrally formed on the tip wall between adjacent ones of the plurality of tip leakage control channels, each vane curved toward the trailing edge from a vane leading portion to a vane trailing portion.

6. The airfoil of claim 5 , further comprising a tip rib formed along a pressure side of the tip wall from the airfoil leading edge to the airfoil trailing edge;
wherein at least one of the plurality of curved tip leakage control vanes is contiguous with a suction side of the tip rib and at least one tip leakage control vane has its respective inlet on a suction side of the tip rib.

7. The airfoil of claim 6 , further comprising a tip shelf recessed into a pressure side of the tip rib at a junction of the airfoil pressure sidewall and the tip wall, the tip shelf extending along at least a chordwise portion of the junction between the airfoil leading edge and the airfoil trailing edge.

8. The airfoil of claim 1 , wherein a second chordwise channel width W 2 proximate the recessed outlet is equal to or greater than a chordwise channel width W 1 proximate the inlet.

9. The airfoil of claim 8 , wherein the second chordwise channel width W 2 is equal to a pitch P C .

10. The airfoil of claim 1 , wherein at least one of the plurality of channels includes at least one cooling aperture in fluid communication with an internal cooling cavity.

11. A turbine 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 having a tip floor extending chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls; and
a plurality of tip leakage control vanes distributed chordwise across at least a portion of the tip floor extending between the airfoil leading edge and the airfoil trailing edge, each tip leakage control vane projecting radially outward in a spanwise direction from the tip floor, a leading portion of each tip leakage control vane beginning proximate a junction of the airfoil pressure sidewall and the tip wall, a trailing portion of each tip leakage control vane terminating proximate a junction of the airfoil suction sidewall and the tip wall, and a portion curved toward the airfoil trailing edge between the leading portion and the trailing portion.

12. The airfoil of claim 11 , wherein each control vane leading portion forms leading interior angle β 1 relative to a downstream side of the pressure sidewall, and each control vane trailing portion forms trailing interior angle β 2 relative to a downstream side of the suction sidewall, angle β 2 being less than or equal to β 1 .

13. The airfoil of claim 11 , wherein a corresponding plurality of curved tip leakage control channels are defined at least in part by adjacent ones of the plurality of tip leakage control vanes, an inlet of each channel being defined by respective leading portions of the adjacent control vanes, and an outlet of each channel being defined by respective trailing portions of the adjacent control vanes.

14. The airfoil of claim 11 , further comprising a tip rib extending chordwise from the airfoil leading edge to the airfoil trailing edge, a suction side surface of tip rib contiguous with a leading portion of at least one of the plurality of tip leakage control vanes.

15. The airfoil of claim 14 , further comprising a tip shelf recessed into a pressure side of the tip rib at a junction of the airfoil pressure sidewall and the tip wall, the tip shelf extending along at least a chordwise portion of a junction between the airfoil leading edge and the airfoil trailing edge.

16. The airfoil of claim 11 , wherein a trailing vane thickness t 2 of at least one of the plurality of tip leakage control vanes is zero along the junction of the suction sidewall and the tip wall.

17. A method for reducing airfoil tip leakage losses, the method comprising:
capturing a plurality of portions of working fluid leakage flow passing over a junction of an airfoil tip and a pressure sidewall in a leakage control channel formed into a radially outer surface of an airfoil tip wall;
redirecting each captured portion of the leakage flow downstream toward an airfoil trailing edge through a curved portion of each tip leakage control channel; and
ejecting the redirected portion of the leakage flow out of each tip leakage control channel into a suction side gas stream below a junction of the airfoil suction sidewall and the radially outer surface of the tip wall;
wherein the curved portion of each channel is curved downstream toward a trailing edge of the airfoil from a channel inlet proximate a pressure sidewall to a channel outlet at a suction sidewall.

18. The method of claim 17 , further comprising directing at least one of the plurality of portions of the captured working fluid tangentially against at least one tip leakage control vane to recover work from the captured working fluid.

19. The method of claim 18 , wherein outwardly facing sidewalls of the tip leakage control vane are defined by inwardly facing sidewalls of chordwise adjacent ones of the plurality of tip leakage control channels.

20. The method of claim 17 , wherein an inlet portion of the at least one tip leakage control channel is substantially perpendicular to, and offset widthwise from, a junction of the tip wall and an airfoil pressure sidewall.

21. The method of claim 17 , further comprising prior to the capturing step, impeding working fluid leakage flow over the airfoil tip wall.

22. The method of claim 21 , wherein the impeding step is performed by directing a coolant flow outward through a plurality of cooling apertures in a tip shelf disposed along at least a chordwise portion of a junction of the tip wall and the airfoil pressure sidewall.

23. The method of claim 17 , wherein the redirecting step increases a downstream tangential momentum c

Assignees

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

Inventors

• Zelesky Mark F
• Aggarwala Andrew S

Classifications

• F01D5/20

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

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title