| 摘要 |
In accordance with the invention there is provided turbine arrangement, particularly a gas turbine arrangement, comprising at least one rotor blade (2) and a turbine disc (5), the rotor blade (2) comprising a root portion (1), the turbine disc (5) comprising at least one slot (40) in which the root portion (1) of the rotor blade (2) is secured. The slot (40) comprises a plurality of opposite pairs of slot lobes (100) and a plurality of opposite pairs of slot fillets (101), and a slot bottom (105) of the slot (40). The slot bottom (105) is arranged to comprise a first convex surface section (102). Furthermore the root portion (1) of the rotor blade (2) comprises a root bottom (50) comprising a first concave surface section (51) corresponding to the first convex surface section (102) of the slot bottom (105). Additionally, the first convex surface section (102) is pierced by an outlet (44) of a cooling duct (42) through the turbine disc (5). |
