Method and apparatus for cooling gas turbine rotor blades

Details Method and apparatus for cooling gas turbine rotor blades Method and apparatus for cooling gas turbine rotor blades

2007-01-23

2007-01-23

Verdier, Christopher (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Method of operation

C416S09700R

Reexamination Certificate

active

10865471

ABSTRACT:
An airfoil for a gas turbine includes a leading edge, a trailing edge a tip plate, a first sidewall extending in radial span between an airfoil root and the tip plate, and a second sidewall connected to the first sidewall at the leading edge and the trailing edges, to define a cooling cavity therein. The sidewall extends in radial span between the airfoil root and the tip plate. The airfoil also includes a plurality of longitudinally spaced apart trailing edge cooling slots arranged in a column extending through the first sidewall. The slots are in flow communication with the cooling cavity and arranged in a non-uniform distribution along the trailing edge so that the number of slots in at least one portion of the trailing edge is greater than a different portion of the trailing edge.

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