Edge coupon including cooling circuit for airfoil

Patent metadata

Field	Value
Publication number	US-10598028-B2
Application number	US-201615334471-A
Country	US
Kind code	B2
Filing date	Oct 26, 2016
Priority date	Oct 26, 2016
Publication date	Mar 24, 2020
Grant date	Mar 24, 2020

Abstract

An edge coupon for an airfoil is provided. The coupon includes: a coupon body including: a coolant feed; an outward leg extending toward an edge of the coupon and fluidly coupled to the coolant feed; a return leg extending away from the edge of the coupon and radially offset from the outward leg along a radial axis of the coupon; a turn for fluidly coupling the outward leg and the return leg; a collection passage fluidly coupled to the return leg; and a coupling region configured to mate with an airfoil body of the airfoil.

First claim

What is claimed is:

1. A trailing edge coupon for a turbomachine airfoil, the coupon comprising:
a coupon body including:
a coolant feed extending radially through the coupon body;
a collection passage extending radially through the coupon body, adjacent the coolant feed;
an outward leg conduit extending axially from the coolant feed, toward a trailing edge of the coupon, the outward leg conduit in direct fluid communication with the coolant feed;
a return leg conduit extending axially away from the trailing edge of the coupon, toward the collection passage, and radially offset from the outward leg conduit along a radial axis of the coupon, the return leg conduit in direct fluid communication with the collection passage;
a turn conduit fluidly coupling the outward leg conduit and the return leg conduit, the turn conduit positioned adjacent the trailing edge of the coupon; and
a coupling region configured to mate with an airfoil body of the turbomachine airfoil.

2. The trailing edge coupon of claim 1 , wherein the coupon includes at least one pre-sintered preform material.

3. The trailing edge coupon of claim 1 , wherein the coolant feed is configured to fluidly couple to a coolant feed in the airfoil body of the turbomachine airfoil, and the collection passage is configured to fluidly couple to a coolant passage in the airfoil body of the turbomachine airfoil.

4. The trailing edge coupon of claim 1 , wherein the coupling region is positioned at a forward end of the coupon, and couples to a trailing edge of the airfoil body of the turbomachine airfoil.

5. The trailing edge coupon of claim 1 , wherein the coupling region is positioned at a side of the coupon, and couples to one of a pressure side and a suction side of the airfoil body of the turbomachine airfoil.

6. The trailing edge coupon of claim 1 , wherein the coupon body includes a first section and a second section that collectively form the coupon body.

7. The trailing edge coupon of claim 6 , wherein the first section and second section are brazed together, and the coupon is brazed to the airfoil body of the turbomachine airfoil.

8. The trailing edge coupon of claim 1 , wherein the radial offset of the outward leg conduit from the return leg conduit is selected from the group consisting of: radially outward from the return leg conduit and radially inward from the return leg conduit.

9. The trailing edge coupon claim 1 , wherein the return leg conduit is a different size as compared to the outward leg conduit.

10. The trailing edge coupon of claim 1 , wherein the return leg conduit is circumferentially offset relative to the outward leg conduit.

11. The trailing edge coupon of claim 10 , wherein the circumferential offset is selected from the group consisting of the outward leg conduit extending along a suction side of the airfoil body and the return leg conduit extending along a pressure side of the airfoil body, and the outward leg conduit extending along the pressure side of the airfoil body and the return leg conduit extending along the suction side of the airfoil body.

12. A turbomachine airfoil, comprising:
an airfoil body; and
a coupon having a coupon body including:
a coolant feed extending radially through the coupon body;
a collection passage extending radially through the coupon body, adjacent the coolant feed;
an outward leg conduit extending axially from the coolant feed, toward a trailing edge of the coupon, the outward leg conduit in direct fluid communication with the coolant feed;
a return leg conduit extending axially away from the trailing edge of the coupon, toward the collection passage, and radially offset from the outward leg conduit along a radial axis of the coupon, the return leg conduit in direct fluid communication with the collection passage;
a turn conduit fluidly coupling the outward leg conduit and the return leg conduit, the turn conduit positioned adjacent the trailing edge of the coupon; and
a coupling region configured to mate with the airfoil body.

13. The turbomachine airfoil of claim 12 , wherein the coupon includes at least one pre-sintered preform material.

14. The turbomachine airfoil of claim 12 , wherein the coolant feed is configured to fluidly couple to a coolant feed in the airfoil body, and the collection passage is configured to fluidly couple to a coolant passage in the airfoil body.

15. The turbomachine airfoil of claim 12 , wherein the coupling region is positioned at a forward end of the coupon, and couples to a trailing edge of the airfoil body.

16. The turbomachine airfoil of claim 12 , wherein the coupling region is positioned at a side of the coupon, and couples to one of a pressure side and a suction side of the airfoil body.

17. The turbomachine airfoil of claim 12 , wherein the coupon body includes a first section and a second section that collectively form the coupon body, and
wherein the first section and second section are brazed together, and the coupon is brazed to the airfoil body.

18. The turbomachine airfoil of claim 12 , further comprising a flow of coolant passing through the coolant feed, the outward leg conduit, the turn conduit and the return leg conduit, and into the collection passage, and from the collection passage to at least one cooling circuit of the airfoil body of the airfoil.

19. The turbomachine airfoil of claim 18 , wherein the at least one cooling circuit provides at least one of film cooling, convection cooling, or impingement cooling.

20. A turbine system, comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, the turbine component including a plurality of turbine blades, at least one of the plurality of turbine blades including a turbine blade including an airfoil body; and
a coupon coupled to a trailing edge of the airfoil body of the turbine blade, the coupon having a coupon body including:
a coolant feed extending radially through the coupon body,
a collection passage extending radially through the coupon body, adjacent the coolant feed,
an outward leg conduit extending axially from the coolant feed, toward a trailing edge of the coupon, the outward leg conduit in direct fluid communication with the coolant feed,
a return leg conduit extending axially away from the trailing edge of the coupon, toward the collection passage, and radially offset from the outward leg conduit along a radial axis of the coupon, the return leg conduit in direct fluid communication with the collection passage,
a turn conduit for fluidly coupling the outward leg conduit and the return leg conduit, the turn conduit positioned adjacent the trailing edge of the coupon,
a coupling region configured to mate with the airfoil body of the at least one turbine blade of the plurality of turbine blades.

21. An edge coupon for a turbomachine airfoil, the coupon comprising:
a coupon body including:
a coolant feed extending radially through the coupon body;
a collection passage extending radially through the coupon body, adjacent the coolant feed;
an outward leg conduit extending axially from the coolant feed, toward an edge of the coupon, the outward leg conduit in direct fluid communication with the coolant feed;
a return leg conduit extending axially away from the edge of the coupon, toward the collection passage, and radially offset from the outward leg conduit along a radial axis of the coupon, the return leg conduit in direct fluid communication with the collection passage;
a turn conduit

Assignees

• Gen Electric

Inventors

• Hoskin Robert Frank
• Weber David Wayne
• Foster Gregory Thomas

Classifications

• F05D2230/22

  by sintering · CPC title

• F05D2240/304

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

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2230/237

  Brazing · CPC title

• F01D5/147

  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 title