NOZZLE BAND OVERHANG COOLING

摘要

The present invention is unique nozzle assembly for a high pressure turbine of a gas turbine engine. The nozzle assembly includes a plurality of circumferentially spaced vanes and a nozzle band. The nozzle band supports the vanes and includes a mounting flange extending radially from the nozzle band and adapted to be secured to the gas turbine engine. The nozzle band has an overhang portion axially downstream of the mounting flange. A pin fin bank is formed within the overhang portion for allowing cooling fluid to flow therethrough to cool the overhang portion.