Partially wrapped trailing edge cooling circuit with pressure side serpentine cavities

Patent metadata

Field	Value
Publication number	US-10273810-B2
Application number	US-201615334501-A
Country	US
Kind code	B2
Filing date	Oct 26, 2016
Priority date	Oct 26, 2016
Publication date	Apr 30, 2019
Grant date	Apr 30, 2019

Abstract

A turbine blade airfoil including cooling circuits is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil, where the first pressure side cavity is configured to receive a coolant. The airfoil may also include at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, a trailing edge positioned between the pressure and a suction side, and a trailing edge cooling system positioned adjacent the trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may be configured to 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;
at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity;
a trailing edge positioned between the pressure side and a suction side;
at least one suction side cavity positioned adjacent the suction side; and
a trailing edge cooling system positioned adjacent the trailing edge 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 the trailing edge cooling system is configured to provide the received portion of the coolant to the at least one suction side cavity.

3. The airfoil of claim 2 , further comprising a suction side film hole fluidly coupled to the at least one suction side cavity, the suction side film hole configured to exhaust the received portion of the coolant from the at least one suction side cavity.

4. The airfoil of claim 1 , wherein the at least one suction side cavity further includes at least one obstruction.

5. The airfoil of claim 1 , wherein the first pressure side cavity includes an opening formed in a side wall axially adjacent the outward leg of the trailing edge cooling system the opening fluidly coupling the outward leg to the first pressure side cavity.

6. The airfoil of claim 1 , further comprising a pressure side film hole fluidly coupled to the at least one distinct pressure side cavity, the pressure side film hole configured to exhaust a distinct portion of the coolant received by the at least one distinct pressure side cavity from the first pressure side cavity.

7. 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;
at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity;
a trailing edge positioned between the pressure side and a suction side of the airfoil;
at least one suction side cavity positioned adjacent the suction side; and
a trailing edge cooling system positioned adjacent the trailing edge 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.

8. The turbine blade of claim 7 , wherein the trailing edge cooling system is configured to provide the received portion of the coolant to the at least one suction side cavity.

9. The turbine blade of claim 8 , further comprising a suction side film hole fluidly coupled to the at least one suction side cavity, the suction side film hole configured to exhaust the received portion of the coolant from the at least one suction side cavity.

10. The turbine blade of claim 7 , wherein the at least one suction side cavity of the airfoil further includes at least one obstruction.

11. The turbine blade of claim 7 , wherein the first pressure side cavity of the airfoil includes an opening formed in a side wall axially adjacent the outward leg of the trailing edge cooling system, the opening fluidly coupling the outward leg to the first pressure side cavity.

12. The turbine blade of claim 7 , further comprising a pressure side film hole fluidly coupled to the at least one distinct pressure side cavity of the airfoil, the pressure side film hole configured to exhaust a distinct portion of the coolant received by the at least one distinct pressure side cavity from the first pressure side cavity.

13. 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 a pressure side, the first pressure side cavity configured to receive a coolant;
at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity;
a trailing edge positioned between the pressure side and a suction side of the airfoil;
at least one suction side cavity positioned adjacent the suction side; and
a trailing edge cooling system positioned adjacent the trailing edge and in direct fluid communication with the first pressure side cavity, the trailing edge cooling system including a plurality of cooling circuits, each cooling circuit 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.

14. The turbine system of claim 13 , wherein the first pressure side cavity of the airfoil includes a plurality of openings formed in a side wall axially adjacent the plurality of cooling circuits of the trailing edge cooling system, each of the plurality of openings fluidly coupling one of the plurality of cooling circuits to the first pressure side cavity.

15. The turbine system of claim 13 , wherein each turbine blade of the plurality of turbine blades includes a pressure side film hole fluidly coupled to the at least one distinct pressure side cavity of the airfoil, the pressure side film hole configured to exhaust a distinct portion of the coolant received by the at least one distinct pressure side cavity from the first pressure side cavity.

Assignees

• Gen Electric

Inventors

• Weber David Wayne
• Leary Brendon James

Classifications

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/304

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

• F05D2240/306

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