Turbine blades and turbine blade cooling systems and methods

• US 7,857,587 B2
• Filed: 11/30/2006
• Issued: 12/28/2010
• Est. Priority Date: 11/30/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Reddy, Bhanu Mahasamudram, Correia, Victor Hugo Silva, Manning, Robert Francis
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): YOUNGER, SEAN JERRARD
• Application Number:
  US11/606,731
• Publication Number:
  US 20080131278A1
• Time in Patent Office: 1,489 Days
• Field of Search: 415/173.1, 415/173.6, 416/1, 416/92, 416/96.R, 416/97.R, 416/228, 416/235
• US Class Current: 416/92
• CPC Class Codes: F01D 5/187 Convection cooling
• 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 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip. A system for cooling a blade includes at least one tip shelf hole and at least one tip wall opening for channeling cooling air from an internal cooling circuit toward a stream of hot combustion gases for improved cooling of at least the blade tip.

Claims

1. A turbine blade comprising:

an airfoil including an outer wall extending radially outwardly from a root, the outer wall including pressure and suction sides extending laterally from a leading edge to a trailing edge of the airfoil,

a tip cap extending between the pressure and suction sides and between the leading and trailing edges,

a tip wall extending outwardly from the tip cap, wherein the tip wall includes a recessed portion recessed inboard from the pressure side of the outer wall forming a tip shelf between the outer wall and the recessed portion,

an internal cooling circuit extending within the airfoil and being bounded in part by the tip cap,

at least one tip shelf hole extending through the tip shelf in flow communication with the internal cooling circuit, and

at least one tip wall opening extending through the recessed portion radially outward of the tip shelf in flow communication with the internal cooling circuit.

2. The turbine blade according to claim 1 comprising a plurality of tip wall openings extending through the recessed tip wall portion radially outward of the tip shelf in flow communication with the internal cooling circuit.

3. The turbine blade according to claim 1 wherein the at least one tip wall opening is associated with a centerline, and wherein the centerline is oriented at an acute angle with respect to a generally radially extending line.

4. The turbine blade according to claim 1 wherein the recessed tip wall portion is tapered from a maximum wall thickness at a base thereof to a minimum thickness at a location radially disposed from the base.

5. The turbine blade according to claim 4 wherein the maximum wall thickness is defined at least in part by a first radius associated with an outboard side of the recessed tip wall portion and a second radius associated with an inboard side of the recessed tip wall portion.

6. The turbine blade according to claim 2 wherein the recessed tip wall portion is tapered from a maximum wall thickness at a base thereof to a minimum thickness radially disposed from the base.

7. The turbine blade according to claim 2 comprising a plurality of tip shelf holes extending through the tip shelf in flow communication with the internal cooling circuit, and wherein each of the plurality of tip wall openings is generally disposed in staggered relationship to each of the plurality of tip shelf holes.

8. The turbine blade according to claim 2 wherein the centerlines of each tip wall opening are spaced between about 0.36 and 0.46 mm.

9. A method comprising:

a) channeling cooling air from an internal cooling circuit of an airfoil through at least one tip shelf hole extending through a tip shelf formed between a recessed tip wall portion of a tip wall recessed inboard from a pressure side of an airfoil outer wall and the airfoil outer wall; and

b) channeling cooling air from the internal cooling circuit through at least one tip wall opening extending through the recessed tip wall portion;

wherein the cooling air channeled through the at least one tip wall opening joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the at least one tip shelf hole joins and mixes with the stream of hot combustion gases.

10. The method according to claim 9 and further comprising:

c) channeling cooling air from the internal cooling circuit through a plurality of tip shelf holes extending through the tip shelf; and

d) channeling cooling air from the internal cooling circuit through a plurality of tip wall openings extending through the recessed tip wall portion.

11. The method according to claim 10 wherein in (c), channeling cooling air through the plurality of tip shelf holes includes channeling cooling air through tip shelf holes each having a centerline oriented at an acute angle relative to a generally radially extending line.

12. The method according to claim 9 and further comprising:

c) creating a convection cooling eddy effect in the stream of hot combustion gases wherein at least a portion of the gas stream is re-circulated in the tip region after cooling air from the at least one tip shelf hole and the at least one tip wall hole joins and mixes with the stream of hot combustion gasses.

13. A system comprising:

an internal cooling circuit of an airfoil;

at least one tip shelf hole extending through a tip shelf in flow communication with the internal cooling circuit, wherein the tip shelf is formed between a recessed portion of a tip wall extending outwardly from a tip cap and an outer wall of the airfoil; and

at least one tip wall opening extending through the recessed tip wall portion in flow communication with the internal cooling circuit.

14. The system according to claim 13 and further comprising a plurality of tip shelf holes extending through the tip shelf in flow communication with the internal cooling circuit.

15. The system according to claim 14 and further comprising a plurality of tip wall openings extending through the recessed tip wall portion in flow communication with the internal cooling circuit.

16. The system according to claim 15 wherein the tip wall openings are disposed in staggered relationship relative to the tip shelf holes.