Turbine blade platform with near-wall cooling

• US 7,695,247 B1
• Filed: 09/01/2006
• Issued: 04/13/2010
• Est. Priority Date: 09/01/2006
• Status: Active Grant

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Liang, George
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US11/514,815
• Time in Patent Office: 1,320 Days
• Field of Search: 415115-116, 415/1, 416/95, 416/96.R, 416/96.A, 416/97.R, 416/97.A, 416/193.A, 416/1
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades

Abstract

A turbine blade having a platform and an airfoil extending from the platform. The platform includes a plurality of pressure side cooling channels formed within the platform and extending from a location along the aft edge of the platform. Each cooling channel includes a supply hole connected to the box rim cavity formed below the platform. Each pressure side cooling channel opens into a diffuser positioned along the pressure side edge of the platform to discharge cooling air onto the suction side platform of an adjacent blade. The suction side of the platform has cooling channels with supply holes connected to the box rim cavity and discharge holes positioned along the aft edge of the platform. The pressure side and suction side cooling channels in the platform have a curvature substantially of the same curvature as the airfoil in order to cool the entire platform surface exposed to the hot gas flow.

Claims

1. A turbine rotor blade comprising:

a platform having an outer surface forming a hot gas flow path and an inner surface separating the hot gas flow path from a box rim cavity;

an airfoil extending from the platform;

the airfoil having a pressure side wall and a suction side wall;

the platform having a pressure side edge and a suction side edge, and a forward edge and an aft edge;

a plurality of curved cooling channels on the pressure side of the platform covering the pressure side platform from the pressure side edge to the pressure side wall of the airfoil; and

,

some of the pressure side cooling channels having a wider middle section than other of the pressure side curved cooling channels so that substantially the entire pressure side platform is covered by the pressure side cooling channels.

2. The turbine rotor blade of claim 1, and further comprising:

the pressure side cooling channels each include trip strips extending along each channel from an inlet to an outlet of the channel.

3. The turbine rotor blade of claim 1, and further comprising:

the pressure side cooling channels each have an outlet opening into a diffusion slot that opens onto the outer surface and on the suction side edge of the platform.

4. The turbine rotor blade of claim 3, and further comprising:

the pressure side channels each have an inlet opening into the box rim cavity below the platform.

5. The turbine rotor blade of claim 1, and further comprising:

the pressure side channels are separated by walls with openings along the walls that fluidly connect adjacent cooling channels.

6. The turbine rotor blade of claim 1, and further comprising:

a plurality of curved cooling channels on the suction side of the platform; and

,

the plurality of suction side curved cooling channels covering substantially the entire suction side platform surface.

7. The turbine rotor blade of claim 6, and further comprising:

the suction side channels are formed by walls along an upstream end of the channels and walls along the downstream end of the channels, and with the channels converging into a single channel between the upstream end and the downstream end.

8. The turbine rotor blade of claim 6, and further comprising:

the suction side channels include a plurality of exit cooling holes that open onto a side of the aft edge of the platform.

9. The turbine rotor blade of claim 6, and further comprising:

the suction side cooling channels include a plurality of inlet cooling holes connected to the bottom of the platform.

10. The turbine rotor blade of claim 3, and further comprising:

the diffusion slots are positioned on the platform to discharge film cooling air onto an adjacent turbine rotor blade platform on an aft half of the suction side surface of the platform.

11. The turbine rotor blade of claim 4, and further comprising:

the inlet openings of the pressure side channels are cooling supply and impingement holes and extend along a line substantially parallel to the forward edge of the platform.

12. A turbine rotor blade comprising:

a platform having an outer surface forming a hot gas flow path and an inner surface separating the hot gas flow path from a box rim cavity;

an airfoil extending from the platform;

the airfoil having a pressure side wall and a suction side wall;

the platform having a pressure side edge and a suction side edge, and a forward edge and an aft edge;

a plurality of curved cooling channels on the pressure side of the platform;

the plurality of pressure side curved cooling channels being separated by walls extending a length of the channel; and

,

a plurality of openings in each wall to fluidly connect adjacent cooling channels.

13. The turbine rotor blade of claim 12, and further comprising:

one of the pressure side curved cooling channels having a wider middle section than another of the pressure side curved cooling channels so that substantially the entire pressure side platform is covered by the pressure side cooling channels.

14. The turbine rotor blade of claim 12, and further comprising:

the pressure side cooling channels each include trip strips extending along each channel from an inlet to an outlet of the channel.

15. The turbine rotor blade of claim 12, and further comprising:

the plurality of pressure side curved cooling channels each include an inlet hole connected to the box rim cavity and an outlet opening into a diffusion slot;

the pressure side cooling channels covering substantially the entire surface of the pressure side platform; and

,

the diffusion slots open onto the outer surface of the platform along the pressure side edge of the platform.

16. A turbine rotor blade comprising:

a platform having an outer surface forming a hot gas flow path and an inner surface separating the hot gas flow path from a box rim cavity;

an airfoil extending from the platform;

the airfoil having a pressure side wall and a suction side wall;

the platform having a pressure side edge and a suction side edge, and a forward edge and an aft edge;

a plurality of curved cooling channels in the pressure side of the platform;

each pressure side curved cooling channel having an inlet near to the forward edge of the platform and an outlet opening onto the platform at the pressure side edge;

a plurality of curved suction side cooling channels in the suction side of the platform;

each suction side curved cooling channel having an inlet near to the forward edge of the platform and an outlet opening on a side of the aft edge of the platform; and

,

the curved cooling channels covering substantially the entire platform surface.

17. The turbine rotor blade of claim 16, and further comprising:

the pressure side curved cooling channels being separated by walls that have openings to fluidly connect adjacent curved cooling channels.

18. The turbine rotor blade of claim 16, and further comprising:

the suction side curved cooling channels are formed by walls along an upstream end of the channels and walls along the downstream end of the channels, and with the channels merging into a single channel in the middle section.

19. The turbine rotor blade of claim 18, and further comprising:

the upstream walls and the downstream walls of the suction side curved cooling channels each include an opening to fluidly connect adjacent channels.

20. The turbine rotor blade of claim 19, and further comprising:

supplying cooling air to the platform along the entire forward edge of the platform.