Baffle for the interstage disc cavity of a gas turbine

摘要

The subcavity (55u) between a stator seal assembly (28) and the upstream rotor disc (9) in the interstage disc cavity (13) of a gas turbine (1) is divided into a radially inward region (71) and a radially outward region (73) by an annular baffle (69) that extends from the seal assembly (28) partially across the subcavity (55u) toward the rotor disc (9). The volume of cooling air injected into the interstage disc cavity (13) can be reduced to increase turbine efficiency because the baffle (69) interrupts recirculation in the subcavity (55u) to confine ingress of the hot main gas flow (17) to the radially outward region (73) away from the rotor seals (37 and 41). <IMAGE>