Patent ID: 7165940

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