Airfoil with thermally conductive pins

Patent metadata

Field	Value
Publication number	US-11333022-B2
Application number	US-201916533393-A
Country	US
Kind code	B2
Filing date	Aug 6, 2019
Priority date	Aug 6, 2019
Publication date	May 17, 2022
Grant date	May 17, 2022

Abstract

An airfoil includes a multi-part body and one or more thermally conductive pins. The multi-part body has an interior region and is formed from multiple pieces joined with each other at an interface. The pieces have multiple cavities and at least one of the pieces defines airfoil cooling channels disposed within the interior region of the body. The one or more thermally conductive pins are within the interior region of the body and extend across the interface. Each of the thermally conductive pins has a first segment disposed within a corresponding cavity of a first piece of the multiple pieces and a second segment disposed within a corresponding cavity of a second piece of the multiple pieces.

First claim

What is claimed is:

1. An airfoil comprising:
a multi-part body having an interior region and formed from multiple pieces joined with each other at an interface, the multiple pieces each having multiple cavities, and at least one of the multiple pieces defining airfoil cooling channels disposed within the interior region of the multi-part body, wherein at least some of the airfoil cooling channels are fluidly connected to respective interior ends of at least some of the multiple cavities; and
one or more thermally conductive pins within the interior region of the multi-part body and extending across the interface, wherein each of the one or more thermally conductive pins has a first segment disposed within a corresponding cavity of a first piece of the multiple pieces and a second segment disposed within a corresponding cavity of a second piece of the multiple pieces.

2. The airfoil of claim 1 , wherein the first piece is a base piece and the second piece is a cap piece.

3. The airfoil of claim 1 , wherein the one or more thermally conductive pins within the multiple cavities of the first and second pieces do not extend into the airfoil cooling channels.

4. The airfoil of claim 1 , wherein the one or more thermally conductive pins are entirely disposed within the interior region of the multi-part body.

5. The airfoil of claim 1 , wherein a braze filler material is disposed on the first piece and the second piece at the interface to securely affix the first piece to the second piece.

6. The airfoil of claim 1 , wherein a material composition of the multi-part body is different from a material composition of the one or more thermally conductive pins.

7. The airfoil of claim 6 , wherein the material composition of the one or more thermally conductive pins has a greater thermal conductivity than the material composition of the multi-part body.

8. The airfoil of claim 1 , wherein the one or more thermally conductive pins include one or more of molybdenum, tungsten, tantalum, niobium, iridium, osmium, rhenium, ruthenium, rhodium, platinum, or copper.

9. The airfoil of claim 1 , wherein the one or more thermally conductive pins include molybdenum surrounded by an alumina coating.

10. The airfoil of claim 1 , wherein the multi-part body extends along a length axis from a mounting end of the multi-part body to a distal end of the multi-part body opposite the mounting end, wherein each of the one or more thermally conductive pins is oriented parallel to the length axis of the multi-part body.

11. A method for producing an airfoil comprising:
obtaining first and second pieces of a multi-part body, each of the first and second pieces including a respective mating surface and defining multiple respective cavities that extend parallel to one another and are open at the respective mating surface, wherein the second piece defines a network of cooling channels within an interior region of the second piece, and the network of cooling channels is fluidly connected to respective interior ends of at least some of the multiple cavities in the second piece;
inserting one or more thermally conductive pins into the multiple cavities of the first piece such that each of the one or more thermally conductive pins is received into a different corresponding cavity, wherein each of the one or more thermally conductive pins has a first segment disposed within a corresponding one of the multiple cavities of the first piece and a second segment that projects beyond the mating surface of the first piece; and
coupling the second piece of the multi-part body to the first piece such that the second segment of each of the one or more thermally conductive pins is received into a corresponding cavity of the second piece for aligning the second piece to the first piece.

12. The method of claim 11 , wherein the mating surface of the first piece and the mating surface of the second piece face each other and define an interface upon coupling the second piece to the first piece, the one or more thermally conductive pins extending across the interface.

13. The method of claim 11 , further comprising, subsequent to coupling the second piece to the first piece, brazing the multi-part body to securely affix the second piece to the first piece.

14. The method of claim 11 , wherein, upon coupling the second piece to the first piece, each of the second segments of the one or more thermally conductive pins do not extend past the interior ends of the multiple cavities of the second piece into the network of cooling channels.

15. The method of claim 11 , wherein the first piece of the multi-part body is obtained by forming the first piece to have a material composition that has a lower thermal conductivity than a material composition of the one or more thermally conductive pins.

16. The method of claim 11 , wherein the first piece is a base piece and the second piece is a cap piece, and coupling the second piece of the multi-part body to the first piece comprises attaching the cap piece onto a distal end of the base piece that is opposite a mounting end of the base piece, the mounting end configured to be attached to a hub of a rotor assembly.

17. An airfoil comprising:
a body having exterior surfaces and an interior region, the body defining multiple cavities and a network of cooling channels within the interior region, the multiple cavities being parallel to one another, the network of cooling channels fluidly connected to respective interior ends of the multiple cavities; and
one or more thermally conductive pins disposed within the multiple cavities such that each of the one or more thermally conductive pins is disposed within a different corresponding cavity of the multiple cavities, each of the one or more thermally conductive pins filling at least a majority of the corresponding cavity without extending into the network of cooling channels,
wherein a material composition of the one or more thermally conductive pins has a greater thermal conductivity than a material composition of the body.

18. The airfoil of claim 17 , wherein the multiple cavities of the body extend into the interior region from one of the exterior surfaces of the body.

19. The airfoil of claim 17 , wherein the body is a multi-part body defined by a first piece and a second piece that couple to one another at an interface, wherein a first set of the multiple cavities of the body are defined within the first piece and a second set of the multiple cavities are defined within the second piece, wherein the second set mirrors the first set across the interface to enable each of the one or more thermally conductive pins to be disposed within one corresponding cavity of the first set and one corresponding cavity of the second set.

20. The airfoil of claim 19 , wherein the body extends along a length axis from a mounting end of the body to a distal end of the body opposite the mounting end, the mounting end configured to be attached to a hub of a rotor assembly, wherein the first piece is a base piece that defines a first length of the body from the mounting end to the interface, and the second piece is a cap piece that defines a second length of the body from the interface to the distal end.

Assignees

• Gen Electric

Inventors

• Dyson Thomas Earl
• Hammer Kimberly
• Iverson Jared
• Rawcliffe Gerald
• Willson Patrick
• Suzuki Akane

Classifications

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• B23P2700/06

  Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components · CPC title

• B23P15/006

  turbine wheels · CPC title

• F01D5/147 Primary

  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 title

• F05D2300/172

  Copper alloys · CPC title