Patent ID: 8104292

Claim:
A gas turbine engine apparatus comprising: an annular combustor having a row of fuel injectors; an annular turbine nozzle following said combustor and having a row of vane doublets with axial splitlines therebetween; a row of turbine blades following said nozzle; a duplex turbine shroud surrounding said blades, and comprising a row of different first and second shroud segments alternating circumferentially around said blades; said first segments having a first pattern of first cooling holes clocked with said fuel injectors for receiving hot combustion streaks therefrom over said first cooling holes; and said second segments having a second pattern of second cooling holes clocked offset with said injectors for receiving cold combustion streaks from the spaces therebetween over said second cooling holes, wherein said second cooling holes have smaller diameters than said first cooling holes.