Integral nozzle and shroud segment

摘要

A gas turbine engine component (50) including a nozzle outer band (52), a plurality of nozzle vanes (54) extending inward from the outer band (52), and an inner band (58) extending circumferentially around inner ends of the vanes (54). Further, the component (50) has a shroud (60) integral with the outer band (52) adapted for surrounding a plurality of blades mounted in the engine for rotation about a centerline thereof.