| 摘要 |
A seal assembly (50) between a disc cavity (36) and a hot gas path ( 34) in a gas turbine engine includes a rotating blade assembly (18) having a plurality of blades (20) that rotate with a turbine rotor (24) during operation of the engine, and a stationary vane assembly (12) having a plurality of vanes (14) and an inner shroud (16). The inner shroud 16 includes a radially outwardly facing first surface (40), a radially inwardly facing second surface (46), and a plurality of grooves (60) extending into the second surface (46). The grooves (60) are arranged such that a space having a component in a circumferential direction is defined between adjacent grooves (60). During operation of the engine, the grooves (60) guide purge air out of the disc cavity (36) toward the hot gas path (34) such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path (34). |
