Durable turbine nozzle
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[0023]Illustrated in FIG. 1 is a portion of an exemplary aircraft gas turbine engine 10 which is axisymmetrical about a longitudinal or axial centerline axis 12. The engine includes a fan and a multistage compressor (not shown) through which air 14 is pressurized in turn, with the fan air being used for propelling an aircraft in flight, and the air pressurized in the compressor being mixed with fuel and ignited in a combustor 16, only the aft portion thereof being illustrated, for generating hot combustion gases 18 which flow downstream therefrom.
[0024]The engine includes a high pressure turbine 20 having a first stage stator nozzle 22 followed in turn by a row of first stage turbine rotor blades 24 extending radially outwardly from a supporting disk. The combustion gases 18 are channeled through the nozzle vanes 22 and blades 24 for powering the compressor in a conventional manner.
[0025]Disposed immediately downstream from the first stage blades 24 is a second stage turbine stator ...
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