GAS TURBINE ENGINE AND COOLED FLOWPATH COMPONENT THEREFOR

• US 20120201653A1
• Filed: 12/24/2011
• Published: 08/09/2012
• Est. Priority Date: 12/30/2010
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Rhodes, Jeffrey F., Moga, Corina, Layne, Jerry
• Granted Patent: US 10,060,264 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/126 Baffles or ribs
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2250/18 patterned
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Claims

1. A turbine flowpath component for a gas turbine engine, comprising:

a spar; and

a coversheet configured to at least partially enclose the spar, and configured for mating engagement with the spar;

wherein the coversheet includes a plurality of pedestals formed therein and extending toward the spar; and

wherein the plurality of pedestals are configured to form a cooling circuit for cooling air.

2. The turbine flowpath component of claim 1, wherein the turbine flowpath component is defined by a pressure side and a suction side;

wherein the coversheet is configured for engagement with the spar on the suction side.

3. The turbine flowpath component of claim 1, further comprising a first plurality of cooling air passages interleaved with a second plurality of cooling air passages, wherein the first plurality of cooling air passages delivers cooling air to a first location;

and wherein the second plurality of cooling air passages delivers cooling air to a second location different from the first location.

4. The turbine flowpath component of claim 3, wherein the first plurality of cooling air passages is configured to deliver cooling air to the cooling circuit.

5. The turbine flowpath component claim 3, wherein the turbine flowpath component is defined by a pressure side and a suction side;

and wherein the second plurality of cooling air passages is configured to transfer cooling air from the suction side to the pressure side.

6. The turbine flowpath component of claim 5, wherein the second plurality of cooling air passages are configured to discharge cooling air for film cooling on the pressure side.

7. The turbine flowpath component of claim 1, wherein the turbine flowpath component is defined by a pressure side and a suction side, wherein the spar forms a cavity between the pressure side and the suction side, further comprising a plurality of hollow pins extending between the pressure side and the suction side and bridging the cavity, wherein the hollow pins are oval in cross-sectional shape.

8. The turbine flowpath component of claim 7, wherein the hollow pins are configured to transmit cooling air directly from the suction side to the pressure side.

9. The turbine flowpath component of claim 1, wherein the pedestals are bonded to the spar.

10. A gas turbine engine, comprising:

a turbine having a turbine flowpath component, wherein the turbine flowpath component is defined by a first side and a second side opposite the first side; and

wherein the turbine flowpath component includes a first plurality of internal cooling air passages and a second plurality of internal cooling air passages, wherein the first plurality of internal cooling air passages is interleaved with the second plurality of internal cooling air passages;

wherein the first plurality of internal cooling air passages crosses over the second plurality of internal cooling air passages;

wherein the first plurality of internal cooling air passages is configured to deliver cooling air toward the first side; and

wherein the second plurality of internal cooling air passages is configured to deliver cooling air toward the second side.

11. The gas turbine engine of claim 10, further comprising a spar, wherein the first plurality of internal cooling air passages and the second plurality of internal cooling air passages are disposed within the spar.

12. The gas turbine engine of claim 11, wherein the spar includes a wall defining a cooling air supply cavity, wherein at least one of the first plurality of internal cooling air passages and the second plurality of internal cooling air passages penetrates the wall and is configured to deliver cooling air from the cooling air supply cavity through the wall to a respective at least one of the first side and the second side.

13. The gas turbine engine of claim 11, further comprising a coversheet configured to at least partially enclose the spar;

and a cooling circuit defined between the spar and the coversheet at the first side, wherein the first plurality of internal cooling air passages is configured to supply cooling air to the cooling circuit.

14. The gas turbine engine of claim 13, wherein the coversheet includes a plurality of pedestals formed therein on the first side;

wherein the pedestals extend toward the spar and define the cooling circuit between the spar and the coversheet.

15. The gas turbine engine of claim 14, wherein the turbine flowpath component has a trailing edge;

and wherein the pedestals are disposed adjacent to the trailing edge.

16. The gas turbine engine of claim 13, wherein the coversheet includes an opening on the second side;

and wherein the second plurality of internal cooling air passages is configured to supply cooling air to the opening.

17. The gas turbine engine of claim 12, further comprising a plurality of hollow pins extending between the first side and the second side and bridging the cooling air supply cavity, wherein the hollow pins are oval in cross-sectional shape;

and wherein the hollow pins are configured to transmit cooling air directly from the first side to the second side.

18. The gas turbine engine of claim 10, wherein the turbine flowpath component is configured as a turbine airfoil.

19. The gas turbine engine of claim 10, wherein the turbine flowpath component is configured as a turbine vane.

20. A flowpath component for a gas turbine engine, comprising:

a spar defined by a first side, a second side, and a cooling air supply cavity formed between the first side and the second side; and

means for cooling the flowpath component using cooling air supplied by the cooling air supply cavity.