Cooled airfoil trailing edge and method of cooling the airfoil trailing edge

Patent metadata

Field	Value
Publication number	US-9732617-B2
Application number	US-201314089920-A
Country	US
Kind code	B2
Filing date	Nov 26, 2013
Priority date	Nov 26, 2013
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.

First claim

The invention claimed is:

1. An airfoil comprising:
a leading edge;
a trailing edge;
a suction side and a pressure side, wherein a downstream edge of the pressure side lies upstream of a downstream edge of the suction side;
at least one internal cooling channel defined between the suction side and the pressure side and configured to convey a cooling fluid;
a plurality of land extensions extending only from the downstream edge of the pressure side to the downstream edge of the suction side;
a plurality of trailing edge bleed slots defined therebetween the plurality of land extensions and in fluid communication with the at least one internal cooling channel, wherein the plurality of trailing edge bleed slots are exposed proximate to the trailing edge of the airfoil, the at least one cooling channel configured to supply the cooling fluid towards the plurality of trailing edge bleed slots; and
one or more obstruction features disposed within the at least one internal cooling channel, wherein a furthest downstream edge of the one or more obstruction features is in a same plane as a most upstream edge of the plurality of land extensions, and the plane also coincides with the downstream edge of the pressure sidewall, the one or more obstruction features configured so that a flow of the cooling fluid impinges on an upstream portion of the one or more obstruction features to distribute the flow of the cooling fluid toward radially outer portions of each of the plurality of trailing edge bleed slots and provide distributed cooling to the plurality of trailing edge bleed slots.

2. The airfoil of claim 1 , further comprising a pin array positioned within the at least one internal cooling channel to distribute the flow of the cooling fluid towards the trailing edge.

3. The airfoil of claim 1 , wherein the one or more obstruction features comprise a predefined substantially polygon shape.

4. The airfoil of claim 1 , wherein the one or more obstruction features are configured as substantially elliptical obstruction features.

5. The airfoil of claim 1 , wherein the one or more obstruction features are configured as substantially circular obstruction features.

6. The airfoil of claim 3 , wherein the one or more obstruction features are disposed laterally offset within the at least one internal cooling channel, relative to the plurality of trailing edge bleed slots, to asymmetrically distribute the flow of the cooling fluid to the plurality of trailing edge bleed slots.

7. The airfoil of claim 3 , wherein the one or more obstruction features are disposed centrally within the at least one internal cooling channel, relative to the plurality of trailing edge bleed slots, to symmetrically distribute the flow of the cooling fluid relative to the plurality of trailing edge bleed slots.

8. The airfoil of claim 3 , wherein the one or more obstruction features are each configured as a multi-element obstruction feature.

9. The airfoil of claim 1 , wherein the airfoil comprises a gas turbine blade airfoil.

10. The airfoil of claim 1 , wherein the airfoil comprises a gas turbine vane airfoil.

11. An airfoil comprising:
a leading edge;
a trailing edge;
a suction side and a pressure side, wherein a downstream edge of the pressure side lies upstream of a downstream edge of the suction side;
at least one internal cooling channel defined between the suction side and the pressure side and configured to convey a cooling fluid;
a plurality of land extensions extending only from the downstream edge of the pressure side to the downstream edge of the suction side;
a plurality of trailing edge bleed slots defined therebetween the plurality of land extensions and in fluid communication with the at least one internal cooling channel, wherein
the plurality of trailing edge bleed slots are exposed proximate to the trailing edge of the airfoil, the at least one cooling channel configured to supply the cooling fluid towards the plurality of trailing edge bleed slots;
a pin array positioned within the at least one internal cooling channel to distribute the flow of the cooling fluid towards the trailing edge; and
one or more obstruction features disposed within the at least one internal cooling channel, wherein a furthest downstream edge of the one or more obstruction features is in a same plane as a most upstream edge of the plurality of land extensions, and the plane also coincides with the downstream edge of the pressure sidewall, the one or more obstruction features comprising a predefined shape and configured so that a flow of the cooling fluid impinges on an upstream portion of the one or more obstruction features to distribute the flow of the cooling fluid toward radially outer portions of each of the plurality of trailing edge bleed slots and provide distributed cooling to the plurality of trailing edge bleed slots.

12. The airfoil of claim 11 , wherein the one or more obstruction features are configured as substantially elliptical obstruction features, substantially circular obstruction features, substantially polygon shaped features mimicking a shape of one of the plurality of trailing edge bleed slots, or a combination of substantially elliptical obstruction features, substantially circular obstruction features and substantially polygon shaped features.

13. The airfoil of claim 12 , wherein the one or more obstruction features are disposed laterally offset within the at least one internal cooling channel, relative to the plurality of trailing edge bleed slots, to asymmetrically distribute the flow of the cooling fluid to the plurality of trailing edge bleed slots.

14. The airfoil of claim 12 , wherein the one or more obstruction features are disposed centrally within the at least one internal cooling channel, relative to the plurality of trailing edge bleed slots, to symmetrically distribute the flow of the cooling fluid to the plurality of trailing edge bleed slots.

15. The airfoil of claim 11 , wherein the one or more obstruction features are each configured as a multi-element obstruction feature.

16. The airfoil of claim 11 , wherein the airfoil comprises one of a gas turbine blade airfoil or a gas turbine vane airfoil.

17. A method of cooling an airfoil comprising a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, wherein a downstream edge of the pressure side lies upstream of a downstream edge of the suction side, the method comprising:
supplying the cooling fluid from the at least one internal cooling channel toward a plurality of trailing edge bleed slots in fluid communication with the at least one internal cooling channel, each of the plurality of trailing edge bleed slots defined by a plurality of land extensions extending only from the downstream edge of the pressure side to the downstream edge of the suction side,
wherein the plurality of trailing edge bleed slots are exposed proximate to a trailing edge of the airfoil,
wherein the at least one internal cooling channel includes a plurality of obstruction features disposed within the at least one internal cooling channel, wherein a furthest downstream edge of the one or more obstruction features is in a same plane as a most upstream edge of the plurality of land extensions, and the plane also coincides with the downstream edge of the pressure sidewall, the plurality of obstruction features configured so that a flow of the cooling fluid impinges on an upstream portion of the one or more obstruction features to distribute the flow of the cooling fluid towa

Assignees

• Gen Electric

Inventors

• Wang Guanghua
• Bunker Ronald Scott
• Bailey Jeremy Clyde
• Delancey James Peter
• Helmer David Benjamin

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2250/141

  circular · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title