Patent ID: 8281604

Claim:
A gas turbine engine comprising: an annular combustor configured for discharging combustion gases; a turbine nozzle following said combustor and including a row of nozzle vanes extending radially between laterally surrounding inner and outer bands; a row of turbine rotor blades following said nozzle for extracting energy from said combustion gases; each of said nozzle vanes including circumferentially opposite pressure and suction sidewalls extending radially in span between said bands and extending axially in chord between opposite leading and trailing edges; and each vane further including inner and outer patterns of corresponding inner and outer cooling holes distributed along said leading edge and inclined oppositely inwardly toward said inner band and outwardly toward said outer band, respectively, wherein said inner cooling holes are disposed along a lower half of said leading edge adjacent said inner band, and said outer cooling holes are disposed along an upper half of said leading edge adjacent said outer band.