Airfoil assembly with a cooling circuit

Patent metadata

Field	Value
Publication number	US-11401817-B2
Application number	US-201615343849-A
Country	US
Kind code	B2
Filing date	Nov 4, 2016
Priority date	Nov 4, 2016
Publication date	Aug 2, 2022
Grant date	Aug 2, 2022

Abstract

An airfoil assembly for a gas turbine engine including a blade, platform, and dovetail. The airfoil assembly further includes a cooling circuit including an interior chamber of the dovetail having fluid communication with the exterior of the airfoil assembly or with an interior chamber of the blade and at least one cooling passage.

First claim

What is claimed is:

1. An airfoil assembly for a turbine engine comprising:
a. a platform having first and second opposing surfaces;
b. an airfoil extending from the first surface and having an outer wall bounding an interior and defining a pressure side and a suction side extending axially between a leading edge to a trailing edge to define a chord-wise direction and extending radially between a root and a tip to define a span-wise direction, with the root being adjacent the platform;
c. a cooling circuit passing through the platform and into the interior of the airfoil, the cooling circuit extending in the span-wise direction through the platform and into the interior of the airfoil; and
d. at least one curvilinear cooling passage having a single continuous bend including and extending between an inlet in direct fluid communication with the cooling circuit and an outlet on the first surface.

2. The airfoil assembly of claim 1 wherein the at least one curvilinear cooling passage defines a centerline, which at the outlet, defines an included angle with the first surface.

3. The airfoil assembly of claim 2 wherein the included angle is less than 30 degrees.

4. The airfoil assembly of claim 3 wherein the included angle is less than 20 degrees.

5. The airfoil assembly of claim 1 wherein the at least one curvilinear cooling passage defines a plurality of curvilinear cooling passages, each extending between a corresponding inlet and outlet.

6. The airfoil assembly of claim 5 wherein at least some of the plurality of curvilinear cooling passages have their outlets aligned with a flow streamline about the airfoil.

7. The airfoil assembly of claim 1 wherein the at least one curvilinear cooling passage is cast within the platform.

8. The airfoil assembly of claim 1 wherein the outlet is located in a rear half of the airfoil in the chord-wise direction.

9. The airfoil assembly of claim 8 wherein the outlet is located above the suction side.

10. The airfoil assembly of claim 1 wherein the outlet is positioned at the root of the airfoil.

11. The airfoil assembly of claim 1 wherein the outlet on the first surface is located within the interior of the airfoil.

12. A blade for a turbine engine comprising:
a. a platform having first and second opposing surfaces;
b. a dovetail extending from the second surface;
c. an airfoil extending from the first surface and having an outer wall bounding an interior and defining a pressure side and a suction side extending axially between a leading edge to a trailing edge to define a chord-wise direction and extending radially between a root and a tip to define a span-wise direction, with the root being adjacent the platform;
d. a cooling circuit passing through the dovetail, platform and into the interior of the airfoil, the cooling circuit extending in the span-wise direction a distance through the dovetail, platform, and into the interior of the airfoil; and
e. at least one curvilinear cooling passage having a single continuous bend including and extending between an inlet in direct fluid communication with the cooling circuit and an outlet on the first surface.

13. The blade of claim 12 wherein the at least one curvilinear cooling passage defines a centerline, which at the outlet, defines an included angle with the first surface.

14. The blade of claim 13 wherein the included angle is less than 30 degrees.

15. The blade of claim 14 wherein the included angle is less than 20 degrees.

16. The blade of claim 12 wherein the at least one curvilinear cooling passage defines a plurality of curvilinear cooling passages, each extending between a corresponding inlet and outlet.

17. The blade of claim 16 wherein at least some of the plurality of curvilinear cooling passages have their outlets aligned with a flow streamline about the airfoil.

18. The blade of claim 12 wherein the at least one curvilinear cooling passage is cast within the platform.

19. The blade of claim 12 wherein the outlet is located in a rear half of the airfoil in the chord-wise direction.

20. The blade of claim 19 wherein the outlet is located above the suction side.

21. The blade of claim 12 wherein the at least one curvilinear cooling passage extends through the dovetail and the platform.

22. A method of cooling an airfoil for a turbine engine, the method comprising:
supplying cooling air to a cooling circuit within a dovetail and a platform having first and second opposing surfaces, wherein the airfoil extends from the first surface and the dovetail extends from the second surface, the cooling circuit extending in a span-wise direction a distance through the dovetail, the platform and into an interior of the airfoil;
passing the cooling air through a curvilinear passage having a single continuous bend in the platform, the single continuous bend of the curvilinear passage including and extending between an inlet below the second surface at a first height and an outlet at the first surface at a second height, with the inlet in direct fluid communication with the cooling circuit; and
emitting the cooling air through the outlet of the curvilinear passage, with the outlet located in the first surface adjacent a root of the airfoil.

23. The method of claim 22 further comprising emitting the cooling air from the outlet along a path forming an included angle of less than 30 degrees relative to the platform.

24. The method of claim 23 wherein the included angle is less than 20 degrees.

25. The method of claim 22 further comprising emitting the cooling air at an aft half of the airfoil.

26. The method of claim 25 further comprising emitting the cooling air adjacent a suction side of the airfoil.

Assignees

• Gen Electric

Inventors

• Hoffman James Michael
• Polizzi Danielle Leigh

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title