Partially wrapped trailing edge cooling circuits with pressure side impingements

Patent metadata

Field	Value
Publication number	US-10301946-B2
Application number	US-201615334517-A
Country	US
Kind code	B2
Filing date	Oct 26, 2016
Priority date	Oct 26, 2016
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

A turbine blade airfoil including various internal cavities that are fluidly coupled is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil. The first pressure side cavity may receive a coolant. The airfoil may also include a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, and at least one channel positioned between and fluidly coupling the first and second pressure side cavities. The channel may be positioned radially between a top surface and a bottom surface of the first and second pressure side cavities. Additionally, the airfoil may include a trailing edge cooling system positioned adjacent a trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may receive a portion of the coolant from the first pressure side cavity.

First claim

What is claimed is:

1. An airfoil for a turbine blade, the airfoil comprising:
a first pressure side cavity positioned adjacent a pressure side, the first pressure side cavity configured to receive a coolant;
a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity;
at least one channel positioned between and fluidly coupling the first pressure side cavity and the second pressure side cavity, the at least one channel positioned radially between a top surface and a bottom surface of:
the first pressure side cavity; and
the second pressure side cavity;

at least one suction side cavity positioned adjacent a suction side, opposite the pressure side; and
a trailing edge cooling system positioned adjacent a trailing edge of the airfoil and in direct fluid communication with the first pressure side cavity, the trailing edge cooling system including:
an outward leg extending axially between the trailing edge and the first pressure side cavity, the outward leg in fluid communication with the first pressure side cavity;
a return leg extending axially between the trailing edge and the at least one suction side cavity, the return leg in fluid communication with the at least one suction side cavity; and

a turn positioned directly adjacent the trailing edge, the turn fluidly coupling the outward leg and the return leg.

2. The airfoil of claim 1 , wherein at least a portion of the first pressure side cavity is positioned between the trailing edge and the second pressure side cavity.

3. The airfoil of claim 1 , wherein the at least one channel further includes a plurality of channels fluidly coupled to the second pressure side cavity.

4. The airfoil of claim 3 , wherein the plurality of channels are positioned between and fluidly couples the first pressure side cavity and the second pressure side cavity.

5. The airfoil of claim 3 , further comprising a third pressure side cavity positioned adjacent the second pressure side cavity, opposite the first pressure side cavity, the third pressure side cavity fluidly coupled to the second pressure side cavity via one of the plurality of channels.

6. The airfoil of claim 3 , wherein the plurality of channels are positioned on an internal wall, opposite the pressure side.

7. The airfoil of claim 1 , wherein a portion of the first pressure side cavity axially extends adjacent the second pressure side cavity.

8. The airfoil of claim 1 , further comprising a pressure side film hole fluidly coupled to the second pressure side cavity, the pressure side film hole configured to exhaust the coolant from the second pressure side cavity.

9. The airfoil of claim 8 , wherein the pressure side film hole is positioned adjacent the channel.

10. The airfoil of claim 1 , wherein the outward leg of the trailing edge cooling system extends substantially perpendicular to the trailing edge.

11. The airfoil of claim 1 , wherein the return leg of the trailing edge cooling system extends substantially perpendicular to the trailing edge.

12. A turbine blade, comprising:
a shank;
a platform formed radially above the shank; and
an airfoil formed radially above the platform, the airfoil including:
a first pressure side cavity positioned adjacent a pressure side, the first pressure side cavity configured to receive a coolant;
a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity;
at least one channel positioned between and fluidly coupling the first pressure side cavity and the second pressure side cavity, the at least one channel positioned radially between a top surface and a bottom surface of:
the first pressure side cavity; and
the second pressure side cavity;

at least one suction side cavity positioned adjacent a suction side, opposite the pressure side; and
a trailing edge cooling system positioned adjacent a trailing edge of the airfoil and in direct fluid communication with the first pressure side cavity, the trailing edge cooling system including:
an outward leg extending axially between the trailing edge and the first pressure side cavity, the outward leg in fluid communication with the first pressure side cavity;
a return leg extending axially between the trailing edge and the at least one suction side cavity, the return leg in fluid communication with the at least one suction side cavity; and
a turn positioned directly adjacent the trailing edge, the turn fluidly coupling the outward leg and the return leg.

13. The turbine blade of claim 12 , wherein the at least one channel further comprising a plurality of channels positioned between and fluidly coupling the first pressure side cavity and the second pressure side cavity.

14. The turbine blade of claim 12 , wherein a portion of the first pressure side cavity axially extends adjacent the second pressure side cavity.

15. The turbine blade of claim 12 , further comprising a pressure side film hole fluidly coupled to the second pressure side cavity of the airfoil, the pressure side film hole configured to exhaust the coolant from the second pressure side cavity.

16. The turbine blade of claim 15 , wherein the at least one channel of the airfoil is fluidly coupled to the second pressure side cavity at least one of:
opposite the pressure side film hole, or
adjacent the pressure side film hole.

17. A turbine system comprising:
a turbine component including a plurality of turbine blades, each of the plurality of turbine blades including:
an airfoil including:
a first pressure side cavity positioned adjacent the pressure side, the first pressure side cavity configured to receive a coolant;
a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity;
at least one channel positioned between and fluidly coupling the first pressure side cavity and the second pressure side cavity, the at least one channel positioned radially between a top surface and a bottom surface of:
the first pressure side cavity; and
the second pressure side cavity;

at least one suction side cavity positioned adjacent the suction side, opposite the pressure side; and
a trailing edge cooling system positioned adjacent a trailing edge of the airfoil and in direct fluid communication with the first pressure side cavity, the trailing edge cooling system including:
an outward leg extending axially between the trailing edge and the first pressure side cavity, the outward leg in fluid communication with the first pressure side cavity;
a return leg extending axially between the trailing edge and the at least one suction side cavity, the return leg in fluid communication with the at least one suction side cavity; and
a turn positioned directly adjacent the trailing edge, the turn fluidly coupling the outward leg and the return leg.

18. The turbine system of claim 17 , wherein the at least one channel of the airfoil further comprises a plurality of channels positioned between and fluidly coupling the first pressure side cavity and the second pressure side cavity.

19. The turbine system of claim 17 , wherein a portion of the first pressure side cavity axially extends adjacent the second pressure side cavity.

20. The turbine system of claim 17 , wherein at least a portion of the first pressure side cavity is positioned between the trailing edge and the second pressure side cavity.

Assignees

• Gen Electric

Inventors

• Weber David Wayne
• Leary Brendon James

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/185 Primary

  Liquid cooling (F01D5/181 takes precedence) · CPC title

• F05D2240/304

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

• F05D2260/202

  by film cooling · CPC title

• F05D2240/306

  related to the suction side of a rotor blade · CPC title