Turbine blade with integrated serpentine and axial tip cooling circuits

• US 8,920,123 B2
• Filed: 12/14/2012
• Issued: 12/30/2014
• Est. Priority Date: 12/14/2012
• Status: Expired due to Fees

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Lee, Ching-Pang
• Primary Examiner(s): Landrum, Ned
• Assistant Examiner(s): SEABE, JUSTIN D
• Application Number:
  US13/714,518
• Publication Number:
  US 20140169962A1
• Time in Patent Office: 746 Days
• Field of Search: 415/115, 416/95, 416/96.R, 416/97.R, 416/90.R, 416/92, 416/232
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• 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 2240/307 related to the tip of a rotor blade
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2250/75 given by its similarity to a letter, e.g. T-shaped
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/2212 by creating turbulence
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface

Abstract

An air cooled turbine blade including leading and trailing edges, and pressure and suction side walls extending between the leading and trailing edges. Leading and trailing edge cooling circuits extend spanwise adjacent to the leading and trailing edges, respectively. A forward flow mid-section serpentine cooling circuit extends spanwise and is located between the leading and trailing edge cooling circuits. An axial tip cooling circuit extends in the chordal direction and is located between a tip cap of the blade and the serpentine cooling circuit at an outer end of the serpentine cooling circuit. The axial tip cooling circuit has a forward end receiving cooling air from a final channel of the serpentine cooling circuit and discharges the cooling air adjacent to the trailing edge.

Claims

1. An air cooled turbine blade comprising:

an airfoil having a leading edge and a trailing edge, and a pressure side wall and a suction side wall, the pressure and suction side walls extend in a chordal direction between the leading and trailing edges and extend spanwise between a blade root and a tip of the airfoil;

a leading edge cooling circuit extending spanwise adjacent to the leading edge;

a trailing edge cooling circuit extending spanwise adjacent to the trailing edge;

a mid-section serpentine cooling circuit extending spanwise and located between the leading edge cooling circuit and the trailing edge cooling circuit for channeling air in a forward direction extending from the trailing edge toward the leading edge, the serpentine cooling circuit including a first channel and a final channel, the first channel receiving cooling air from a first channel root passage;

an axial tip cooling circuit extending in the chordal direction and located between a tip cap and the serpentine cooling circuit at an outer end of the first channel, the axial tip cooling circuit having a forward end receiving cooling air from the final channel of the serpentine cooling circuit and discharging the cooling air adjacent to the trailing edge, wherein the axial tip cooling circuit is defined as a continuous cavity extending from the pressure side wall to the suction side wall between the tip cap and a cavity floor extending in an aft direction from the forward end of the axial tip cooling circuit to a location adjacent to the trailing edge;

a squealer rail extending radially outward from the tip cap to a radially outer blade tip at the pressure and suction side walls; and

wherein pressure and suction wall corners are defined within the axel tip cooling circuit at junctions of the tip cap with the respective pressure and suction side walls, and the tip cap is defined by opposing side portions extending inwardly from the pressure and suction wall corners toward the cavity floor, the opposing side portions each comprising a continuous radial inward angling to form a junction of the opposing side portions at a chordal center of the airfoil, wherein the axial tip cooling circuit has a minimum dimension in the spanwise direction at the chordal center of the airfoil.

2. The turbine blade of claim 1, wherein the final channel of the serpentine cooling circuit is an outwardly flowing channel that extends to the tip cap and connects to the forward end of the axial tip cooling circuit at a bend.

3. The turbine blade of claim 2, wherein the serpentine cooling circuit includes at least one intermediate channel between the first and final channels, and the cooling flow passes through each of the first, intermediate and final channels prior to entering the axial tip cooling circuit at the bend.

4. The turbine blade of claim 3, wherein adjacent channels are separated by legs extending spanwise and extending from the pressure side wall to the suction side wall, and the leading edge cooling circuit and the final channel of the serpentine circuit are separated by a common leg therebetween.

5. The turbine blade of claim 1, including a leading edge root passage providing cooling air to the leading edge cooling circuit and a trailing edge root passage providing cooling air to the trailing edge cooling circuit, wherein the leading edge cooling circuit directs cooling air to the leading edge and the trailing edge cooling circuit provides cooling air exiting the airfoil at a plurality of trailing edge exit passages.

6. The turbine blade of claim 1, wherein the cavity floor defines an outer flow boundary for the serpentine cooling circuit at the outer end of the first channel and for the trailing edge cooling circuit.

7. The turbine blade of claim 1 including rib-like turbulators extending from inner surfaces of the pressure and suction side walls within the axial tip cooling circuit, the turbulators angled in the spanwise and aft directions, with respect to the cavity floor, to create a turbulent flow of the cooling air in the axial tip cooling circuit radially outward toward the tip cap.

8. The turbine blade of claim 7, wherein the turbulators are angled outward from the cavity floor at an angle within a range from about 30 degrees to about 45 degrees.

9. A process for cooling a turbine blade used in a gas turbine engine, the turbine blade including an inward located blade root and an airfoil having an outward located tip comprising a tip cap located at a radially outer end of the tip, the airfoil including a leading edge and a trailing edge with a plurality of trailing edge exit passages to discharge cooling air from the airfoil, wherein the tip cap further comprises a squealer rail extending radially outward from a junction of an outer tip cap surface with a pressure side wall and a suction side wall, the squealer rail extending chordally from the leading edge to the trailing edge, wherein the tip cap is recessed relative to the squealer rail to define a squealer tip cavity,the process comprising:

supplying cooling air to the airfoil via the blade root;

passing a portion of the cooling air through a leading edge cooling circuit to cool the leading edge of the airfoil;

passing a portion of the cooling air through a trailing edge cooling circuit to exit the airfoil through the plurality of exit passages;

passing a portion of the cooling air through a forward flowing serpentine cooling circuit between the leading edge cooling circuit and the trailing edge cooling circuit;

passing the cooling air from a forward end of the serpentine cooling circuit to flow axially within an axial tip cooling circuit toward the trailing edge to provide cooling to the tip cap; and

directing a greater amount air within the axial tip cooling circuit toward portions of the axial cooling circuit adjacent to the pressure and suction side walls of the airfoil than is provided to a chordal center of the axial tip cooling circuit, comprising;

a) providing a reduced spanwise dimension at a chordal center of the airfoil in the axial tip cooling circuit than spanwise dimensions of the axial tip cooling circuit adjacent to the pressure and suction side walls, wherein pressure and suction wall corners are defined within the axial tip cooling circuit at junctions of an inner tip cap surface with the respective pressure and suction side walls and the tip cap is defined by opposing side portions extending inwardly from the pressure and suction wall corners toward the cavity floor, the opposing side portions each comprising a continuous radial inward angling to form a junction of the opposing side portions at the chordal center of the airfoil; and

b) providing rib-like turbulators extending from inner surface of the pressure and suction side walls within the axial tip cooling circuit, the turbulators angled radially outward in the spanwise and aft directions, with respect to the cavity floor, to create a flow of the cooling air in the axial tip cooling circuit radially outward to corners defined at junctions between the pressure and suction walls and the tip cap.

10. The process for cooling the turbine blade of claim 9, wherein the serpentine cooling circuit includes a first channel, at least one intermediate channel and a final channel, wherein the final channel includes an outer end adjacent to the tip cap where the cooling air is passed from the serpentine cooling circuit to the axial tip cooling circuit.

11. The process for cooling the turbine blade of claim 10, wherein cooling air from the serpentine cooling circuit passes along an inner surface of the tip cap, within the axial tip cooling circuit, from a forward location adjacent to the leading edge cooling circuit to a rearward location where it exits the airfoil adjacent to the trailing edge of the airfoil.

12. The process for cooling the turbine blade of claim 11, wherein the portion of cooling air passing through the serpentine cooling circuit is supplied via the blade root to the first channel of the serpentine cooling circuit.

13. The process for cooling the turbine blade of claim 12, wherein an additional portion of the cooling air is supplied directly to the final channel of the serpentine cooling circuit via the blade root.

14. An air cooled turbine blade comprising:

an airfoil having a leading edge and a trailing edge, and a pressure side wall and a suction side wall, the pressure and suction side walls extend in a chordal direction between the leading and trailing edges and extend spanwise between a blade root and a tip of the airfoil;

a leading edge cooling circuit extending spanwise adjacent to the leading edge;

a trailing edge cooling circuit extending spanwise adjacent to the trailing edge;

a mid-section serpentine cooling circuit extending spanwise and located between the leading edge cooling circuit and the trailing edge cooling circuit for channeling air in a forward direction extending from the trailing edge toward the leading edge, the serpentine cooling circuit including a first channel and a final channel, the first channel receiving cooling air from a first channel root passage;

an axial tip cooling circuit extending in the chordal direction and located between a tip cap and the serpentine cooling circuit at an outer end of the first channel, the axial tip cooling circuit having a forward end receiving cooling air from the final channel of the serpentine cooling circuit and discharging the cooling air adjacent to the trailing edge, wherein the axial tip cooling circuit is defined as a continuous cavity extending from the pressure side wall to the suction side wall between the tip cap and a cavity floor extending in an aft direction from the forward end of the axial tip cooling circuit to a location adjacent to the trailing edge;

wherein pressure and suction wall corners are defined within the axial tip cooling circuit at junctions of an inner tip cap surface with the respective pressure and suction side walls, and the tip cap is defined by opposing side portions extending inwardly from the pressure and suction wall corners toward the cavity floor, the opposing side portions each comprising a continuous radial inward angling to form a junction of the opposing side portions at a chordal center of the airfoil, wherein the axial tip cooling circuit has a minimum dimension in the spanwise direction at the chordal center of the airfoil, the tip cap further comprising a squealer rail extending radially outward from a junction of an outer tip cap surface with the pressure and suction side wall, wherein the squealer rail extends chordally from the leading edge to the trailing edge, the tip cap being recessed relative to the squealer rail to define a squealer tip cavity; and

rib-like turbulators extending from inner surfaces of the pressure and suction side walls within the axial tip cooling circuit, the turbulators angled radially outward in the spanwise and aft directions, with respect to the cavity floor, to create a flow of the cooling air in the axial tip cooling circuit radially outward to the pressure and suction wall corners at the tip cap.