Turbine nozzle seal arrangement.

摘要

A gas turbine engine has an annular turbine nozzle which includes a plurality of nozzle segments arranged in an end-to-end circumferential relationship about a central axis of the engine. A nozzle seal arrangement for impeding leakage of high pressure cooling air past the nozzle inner bands into the flow path includes an annular nozzle support flange (60), a band flange (58) attached to each nozzle segment, a continuous seal member (76) having a W-shaped cross-section which extends circumferentially about the central axis, and an annular recess (78) defined in the forward face of the nozzle support flange which extends circumferentially about the central axis and receives and seats the seal member at the aft side thereof. The forward side of the seal member extends past the forward face of the nozzle support flange and engages the aft face of the inner band flange. <IMAGE>