Heat recovery type gas turbine rotor

摘要

PCT No. PCT/JP96/03416 Sec. 371 Date Jul. 8, 1997 Sec. 102(e) Date Jul. 8, 1997 PCT Filed Nov. 21, 1996 PCT Pub. No. WO97/19256 PCT Pub. Date May 29, 1997Disclosed is a gas turbine rotor (5) having multi-stage moving blades, each fitted to a disc (12), characterized in comprising: an inner cavity (9) and an outer cavity (8) provided between each disc (12); a blade cooling passage (6) of each moving blade except a rearmost stage moving blade (4); a cooling steam supply passage (13) extending from a rear portion of the rearmost stage moving blade (4) to a leading edge portion of a foremost stage moving blade (1) in the rotor (5); a bifurcation passage (16) provided in the disc (12) portion of the foremost stage so as to connect at its proximal end to the cooling steam supply passage (13) and to bifurcate at its distal end so that one bifurcation thereof (16a) connects to one end of the blade cooling passage (6) and the other bifurcation (16b) connects to the outer cavity (8); a blade return passage (17) connecting at its proximal end to the other end of the blade cooling passage (6) and at its distal end to the inner cavity (9); a cavity connecting passage (20) for connecting each inner cavity (9); a return passage (11) extending along the cooling steam supply passage (13) from the inner cavity (9) of the rearmost stage moving blade (4); a blade connecting passage (18) provided in each disc (12) except the discs (12) of the foremost stage and the rearmost stage for connecting the blade cooling passage (6) and the outer cavity (8); an inter-cavity passage (19) for connecting the outer cavity (8) and the inner cavity (9) both of the rearmost stage.