Cooling system for the trailing edges of turbine bucket...

Details Cooling system for the trailing edges of turbine bucket... Cooling system for the trailing edges of turbine bucket...

2006-06-27

2006-06-27

Kershteyn, Igor (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Method of operation

C415S115000, C416S09700R, C416S092000

Reexamination Certificate

active

07066716

ABSTRACT:
The cooling system includes a plurality of generally radially extending passages within the airfoil for convectively cooling the airfoil. A predetermined number of the passages exit through the airfoil tip. One or more of the remaining passages exit into a plenum adjacent the trailing edge and airfoil tip region of the airfoil and flow radially inwardly along one or more passageways adjacent the trailing edge region. The passageways exit in openings along the pressure side of the airfoil. In this manner, the trailing edge region is convectively cooled as well as film cooled by the film of air exiting the holes.

REFERENCES:
patent: 5403159 (1995-04-01), Green et al.
patent: 5462405 (1995-10-01), Hoff et al.
patent: 5902093 (1999-05-01), Liotta et al.
patent: 5931638 (1999-08-01), Krause et al.
patent: 5975851 (1999-11-01), Liang
patent: 6220817 (2001-04-01), Durgin et al.
patent: 6224336 (2001-05-01), Kercher
patent: 6491496 (2002-12-01), Starkweather

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