System and method for cooling turbine blades

• US 9,051,842 B2
• Filed: 01/05/2012
• Issued: 06/09/2015
• Est. Priority Date: 01/05/2012
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Smith, Aaron Ezekiel, Penny, Christopher Michael
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US13/344,530
• Publication Number:
  US 20130177446A1
• Time in Patent Office: 1,251 Days
• Field of Search: 416/97.R, 415/115
• US Class Current: 1/1
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2250/131 polygonal
• CPC Class Codes: F05D 2250/323 convergent
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.

Claims

1. A system, comprising:

a turbine blade comprising at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade, wherein the cooling slot comprises;

an entrance coupled to the interior;

a converging section downstream from the entrance, wherein the converging section comprises a first cross-sectional area that decreases in the flow direction; and

an exit disposed along a trailing edge of the turbine blade, wherein the cooling slot comprises at least one of;

only one metering section, wherein the metering section is disposed only downstream from the converging section;

or

the exit of the cooling slot is disposed along the trailing edge on a midline between a pressure sidewall and a suction sidewall, wherein the exit comprises a diverging section;

or

a combination thereof.

2. The system of claim 1, comprising the only one metering section, wherein the metering section is disposed only downstream from the converging section.

3. The system of claim 2, wherein the converging section comprises a first length in the flow direction, the metering section comprises a second length in the flow direction, and the first length is greater than the second length.

4. The system of claim 2, wherein the metering section comprises a second cross-sectional area that is substantially constant in the flow direction.

5. The system of claim 1, wherein the exit is disposed along the trailing edge on the midline between the pressure sidewall and the suction sidewall, wherein the exit comprises the diverging section.

6. The system of claim 5, wherein the diverging section comprises a third cross-sectional area that increases in the flow direction.

7. The system of claim 1, wherein the converging section comprises a height and a width, wherein both the height and the width decrease in the flow direction.

8. The system of claim 7, wherein the height and the width are different from one another.

9. The system of claim 1, wherein a cross-sectional shape of the converging section comprises at least one of a circle, an oval, a square, a rectangle, or a polygon, or a combination thereof.

10. The system of claim 1, comprising a turbine having the turbine blade.

11. The system of claim 1, wherein the cooling slot is symmetrical about the midline between the pressure sidewall and the suction sidewall.

12. The system of claim 1, wherein the cooling slot comprises:

the metering section disposed only downstream from the converging section; and

the exit disposed along the trailing edge on the midline between the pressure sidewall and the suction sidewall.

13. A system, comprising:

a rotary blade, comprising;

a leading edge;

a trailing edge;

a pressure sidewall;

a suction sidewall;

a cooling cavity disposed between the pressure sidewall and the suction sidewall; and

a plurality of cooling slots coupled to cooling cavity, wherein the plurality of cooling slots is configured to pass a coolant in a flow direction through the trailing edge, and each slot of the plurality of cooling slots comprises;

a converging section comprising a first cross-sectional area that decreases in the flow direction;

only one metering section, wherein the metering section is coupled to the converging section, wherein the metering section is disposed only downstream from the converging section, and the metering section comprises a second cross-sectional area that is substantially constant in the flow direction; and

an exit disposed along the trailing edge on a midline between the pressure sidewall and the suction sidewall, wherein the exit comprises a diverging section.

14. The system of claim 13, wherein the exit is centered directly on the midline.

15. The system of claim 13, wherein each converging section comprises a height and a width, wherein both the height and the width decrease in the flow direction.

16. The system of claim 13, wherein each converging section comprises a first length in the flow direction, each metering section comprises a second length in the flow direction, and a ratio of the first length to the second length is greater than approximately 5:

1.

17. The system of claim 13, wherein the diverging section comprises a third cross-sectional area that increases in the flow direction.

18. The system of claim 13, comprising a turbomachine having the rotary blade, wherein the rotary blade is disposed on a rotor.

19. A method, comprising:

forming a ceramic turbine blade core;

inserting the core into a die; and

casting a turbine blade between the core and the die with a pressure sidewall and a suction sidewall coupled together at a leading edge and a trailing edge, wherein the turbine blade comprises a plurality of cooling slots configured to pass a coolant in a flow direction through the trailing edge, and each slot of the plurality of cooling slots comprises;

a converging section comprising a first cross-sectional area that decreases in the flow direction;

a metering section coupled to the converging section; and

an exit disposed along the trailing edge, wherein each slot of the plurality of cooling slots comprises at least one of;

only the one metering section, wherein the metering section is disposed only downstream from the converging section;

or

the exit is disposed along the trailing edge on a midline between the pressure sidewall and the suction sidewall, wherein the exit comprises a diverging section;

or

a combination thereof.

20. The method of claim 19, wherein the exit is disposed along the trailing edge on the midline between the pressure sidewall and the suction sidewall, wherein the exit is centered on the midline.

21. The method of claim 19, wherein the first cross-sectional area of the converging section decreases in at least two dimensions.

22. The method of claim 19, wherein the converging section comprises a first length in the flow direction, the metering section comprises a second length in the flow direction, and the first length is greater than the second length.

23. The method of claim 19, wherein the metering section is disposed between the converging section and the diverging section.