COOLING STRUCTURES FOR TURBINE ROTOR BLADE TIPS

• US 20140037458A1
• Filed: 08/03/2012
• Published: 02/06/2014
• Est. Priority Date: 08/03/2012
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Lacy, Benjamin Paul, Good, Randall Richard, Brzek, Brian Gene
• Granted Patent: US 9,273,561 B2
• Time in Patent Office: Days
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F05D 2250/182 crenellated, notched

Abstract

A rotor blade for a turbine of a combustion turbine engine having an airfoil that includes a pressure and a suction sidewall defining an outer periphery and a tip portion defining an outer radial end. The tip portion includes a rail that defines a tip cavity. The airfoil includes an interior cooling passage configured to circulate coolant. The rotor blade further includes: a slotted portion of the rail; and at least one film cooling outlet disposed within at least one of the pressure sidewall and the suction sidewall of the airfoil. The film cooling outlet includes a position that is adjacent to the tip portion and in proximity to the slotted portion of the rail.

Claims

1. A rotor blade for a turbine of a combustion turbine engine, the rotor blade comprising an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery and a tip portion defining an outer radial end, the tip portion including a rail that defines a tip cavity, wherein the airfoil includes an interior cooling passage configured to circulate coolant through the airfoil during operation, the rotor blade comprising:

a slotted portion of the rail; and

at least one film cooling outlet disposed within at least one of the pressure sidewall and the suction sidewall of the airfoil, the film cooling outlet comprising a position that is adjacent to the tip portion and in proximity to the slotted portion of the rail.

2. The rotor blade according to claim 1, further comprising a groove extending from a position adjacent to the film cooling outlet toward the slotted portion of the rail;

wherein the tip portion comprises a squealer tip.

3. The rotor blade according to claim 1, wherein:

the interior cooling passage extends from a connection with a coolant source at a root of the rotor blade and the film cooling outlet comprises a port disposed in flow communication with the interior cooling passage;

a tip cap forms a floor of the tip cavity and the rail extends radially from the tip cap;

the slotted portion comprises at least one slot formed through the rail; and

the film cooling outlet is positioned inboard of and near the slot.

4. The rotor blade according to claim 3, further comprising a shelf formed just inboard of the slot on one of the pressure sidewall and the suction sidewall;

wherein the film cooling outlet is positioned on the shelf and oriented such that coolant released therefrom comprises an approximate radial direction.

5. The rotor blade according to claim 3, further comprising a groove extending from the film cooling outlet to the slot.

6. The rotor blade according to claim 3, wherein:

the pressure sidewall and suction sidewall join together at a leading airfoil edge and a trailing airfoil edge, the pressure sidewall and the suction sidewall extending from the root to the squealer tip and defining the interior cooling passage therein;

wherein the rail includes a pressure side rail and a suction side rail, the pressure side rail connecting to the suction side rail at a leading rail edge and a trailing rail edge;

wherein the pressure side rail extends from the leading rail edge to the trailing rail edge such that the pressure side rail approximately aligns with a profile of an outer radial edge of the pressure sidewall; and

wherein the suction side rail extends from the leading rail edge to the trailing rail edge such that the suction side rail approximately aligns with a profile of an outer radial edge of the suction sidewall.

7. The rotor blade according to claim 6, wherein the tip cap is configured to extend axially and circumferentially to connect the outer radial edge of the suction sidewall to the outer radial edge of the pressure sidewall;

and

wherein the rail is disposed at a periphery of the tip cap.

8. The rotor blade according to claim 6, wherein the rail includes an inner rail surface, which faces inwardly and defines the tip cavity, an outer rail surface, which faces outwardly;

and

wherein the rail includes an outboard rail surface, which faces in an outboard direction.

9. The rotor blade according to claim 8, wherein the slot comprises a passageway cut through the thickness of the rail;

wherein the passageway of the slot extends from an opening formed on the outer rail surface to an opening formed on the inner rail surface; and

wherein the passageway of the slot extends radially from an inboard edge of the slot to an opening formed through the outboard rail surface.

10. The rotor blade according to claim 9, wherein the slotted portion of the rail comprises a plurality of regularly spaced slots.

11. The rotor blade according to claim 10, wherein the plurality of slots are disposed in parallel on the suction side.

12. The rotor blade according to claim 10, wherein the plurality of slots are disposed in parallel on the pressure side rail.

13. The rotor blade according to claim 10, wherein the at least one film cooling outlet comprises a plurality of film cooling outlets;

and

wherein for each of the plurality of slots there is at least one corresponding film cooling outlet, each of the corresponding film cooling outlets comprising a position inboard and in proximity to the slot to which the film cooling outlets corresponds.

14. The rotor blade according to claim 10, wherein the at least one film cooling outlet comprises a plurality of film cooling outlets;

and

wherein for each of the plurality of slots there is at least one corresponding film cooling outlet, each of the corresponding film cooling outlets being integrated into the inboard edge of the slot to which the film cooling outlets corresponds.

15. The rotor blade according to claim 10, wherein the at least one film cooling outlet comprises a plurality of film cooling outlets;

and

wherein for each of the plurality of slots there is at least two corresponding film cooling outlets, each of the two corresponding film cooling outlets comprising a position inboard and in proximity to the slot to which each of the two film cooling outlets corresponds.

16. The rotor blade according to claim 13, further comprising a plurality of grooves;

wherein each pair of corresponding film cooling outlets and slots includes a groove stretching therebetween, the groove being configured to direct a flow of coolant expelled from the film cooling outlet to the slot.

17. The rotor blade according to claim 16, wherein each of the plurality of grooves comprises an elongated depression that extends along an outer surface of the rotor blade;

and

wherein each of the plurality of the grooves connects the film cooling outlet to the inboard edge of the slot.

18. The rotor blade according to claim 10, wherein a radial height of the rail comprises a distance from the radial position of the tip cap to the radial position of the outboard face of the rail;

wherein a radial height of the slots comprises a distance from the radial position of the inboard edge of the slot to the radial position of the outboard face of the rail; and

wherein the radial height of each of the plurality of slots is at least 0.5 of the radial height of the rail.

19. A rotor blade for a turbine of a combustion turbine engine, the rotor blade comprising an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery and a tip portion defining an outer radial end, the tip portion including a rail that defines a tip cavity, wherein the airfoil includes an interior cooling passage configured to circulate coolant through the airfoil during operation, the rotor blade comprising:

a slotted portion of the rail, the slotted portion of the rail including a plurality of slots spaced thereon; and

a plurality of film cooling outlets disposed within at least one of the pressure sidewall and the suction sidewall of the airfoil, each of the plurality of film cooling outlets comprising a position that is adjacent to the tip portion and in proximity to the slotted portion of the rail, and each of the plurality of film cooling outlets fluidly communicating with the interior cooling passage;

a plurality of grooves formed between the slotted portion of the rail and the plurality of film cooling outlets;

wherein the plurality of slots and the plurality of film cooling outlets and the plurality of grooves are configured such that each of the plurality of grooves extends in an approximate radially outward direction from a position at or just outboard of one of the plurality of film cooling outlets to a position at or just inboard of an inboard edge of one of the plurality of slots.

20. The rotor blade according to claim 19, wherein each of the plurality of film cooling outlets is incorporated into an inboard edge of the groove;

and

wherein the groove connects to the inboard edge of one of the plurality of slots.

21. The rotor blade according to claim 19, wherein each of the plurality of grooves and each of the plurality of slots comprise a rectangular profile having a substantially constant width.

22. The rotor blade according to claim 19, wherein each of the plurality of grooves comprises a variable width as the groove extends in the radially direction;

and

wherein each of the plurality of slots comprises a variable width as the slot extends in the radially direction.

23. The rotor blade according to claim 19, wherein each of the plurality of grooves and each of the plurality of slots are canted with respect to a radially aligned reference line.

24. The rotor blade according to claim 23, wherein the plurality of grooves and the plurality of slots are canted toward the downstream direction, the downstream direction being relative to a flow direction of working fluid through the turbine;

and

wherein each of the film cooling outlets is configured to release coolant in a direction that approximately corresponds with the cant of the plurality of grooves and the plurality of slots.