Gas turbine engine airfoil cooling passage configuration

• US 10,641,100 B2
• Filed: 04/15/2015
• Issued: 05/05/2020
• Est. Priority Date: 04/23/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Auxier, James T., Jariwala, Parth, Zelesky, Mark F., Teller, Bret M.
• Primary Examiner(s): Verdier, Christopher
• Application Number:
  US14/686,945
• Publication Number:
  US 20160090844A1
• Time in Patent Office: 1,847 Days
• Field of Search: 415115, 416 96 R, 416 96 A, 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: F05D 2250/185 serpentine-like
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.

Claims

1. A component for a gas turbine engine comprising:

pressure and suction walls that together provide an exterior surface and respectively provide pressure and suction sides, a cooling passage in the component includes a serpentine passageway having first and second passes respectively configured to provide fluid flow in opposite directions from one another, the first pass includes first and second portions nested relative to one another and overlapping in a thickness direction, the first portion extends to both of and is at least partially defined by the pressure and suction walls, the second portion extends to both of and is at least partially defined by the pressure and suction walls, the first and second portions adjacent to one another by sharing a common wall that extends to both of the pressure and suction walls, the first portion provided more substantially on the suction side than the pressure side, and the second portion provided more substantially on the pressure side than the suction side.

2. The component according to claim 1, wherein the serpentine passageway includes at least three passes that includes a third pass, the second pass fluidly connected between the first and third passes, the first pass providing any one of the at least three passes.

3. The component according to claim 2, wherein the second pass includes third and fourth portions nested relative to one another and overlapping in a thickness direction, the third and fourth portions adjacent to one another by sharing a common wall, the third portion provided on the suction side, and the fourth portion provided on the pressure side.

4. The component according to claim 3, wherein the third pass includes fifth and sixth portions nested relative to one another and overlapping in a thickness direction, the fifth and sixth portions adjacent to one another by sharing a common wall, the fifth portion provided on the suction side, and the sixth portion provided on the pressure side.

5. The component according to claim 2, wherein the first pass is an up pass from a root toward an airfoil tip.

6. The component according to claim 5, wherein the serpentine passageway is a three pass configuration.

7. The component according to claim 1, wherein the first and second portions are non-quadrilaterally shaped in a chord-wise direction.

8. The component according to claim 1, wherein the first and second portions are substantially triangularly shaped in a chord-wise direction.

9. A gas turbine engine comprising:

compressor and turbine sections; and

an airfoil provided in one of the compressor and turbine sections, the airfoil including pressure and suction walls that together provide an exterior surface and respectively provide pressure and suction sides, a cooling passage in the airfoil includes a serpentine passageway having first and second passes respectively configured to provide fluid flow in opposite directions from one another, the first pass includes first and second portions nested relative to one another and overlapping in a thickness direction, the first portion extends to both of and is at least partially defined by the pressure and suction walls, the second portion extends to both of and is at least partially defined by the pressure and suction walls, the first and second portions adjacent to one another by sharing a common wall that extends to both of the pressure and suction walls, the first portion provided more substantially on the suction side than the pressure side, and the second portion provided more substantially on the pressure side than the suction side.

10. The gas turbine engine according to claim 9, wherein the serpentine passageway includes at least three passes that includes a third pass, the second pass fluidly connected between the first and third passes, the first pass providing any one of the at least three passes.

11. The gas turbine engine according to claim 10, wherein the second pass includes third and fourth portions nested relative to one another and overlapping in a thickness direction, the third and fourth portions adjacent to one another by sharing a common wall, the third portion provided on the suction side, and the fourth portion provided on the pressure side.

12. The gas turbine engine according to claim 11, wherein the third pass includes fifth and sixth portions nested relative to one another and overlapping in a thickness direction, the fifth and sixth portions adjacent to one another by sharing a common wall, the fifth portion provided on the suction side, and the sixth portion provided on the pressure side.

13. The gas turbine engine according to claim 10, wherein the first pass is an up pass from a root toward an airfoil tip.

14. The gas turbine engine according to claim 13, wherein the serpentine passageway is a three pass configuration.

15. The gas turbine engine according to claim 9, wherein the first and second portions are non-quadrilaterally shaped in a chord-wise direction.

16. The gas turbine engine according to claim 9, wherein the first and second portions are substantially triangularly shaped in a chord-wise direction.

17. The gas turbine engine according to claim 9, wherein the airfoil is provided in the turbine section.

18. The gas turbine engine according to claim 17, wherein the airfoil is a turbine blade.