| 摘要 |
Arrangement (66, 112) for a gas turbine (10), comprising: a rotor disk portion (68) comprising an engaging section (70); a blade unit portion (72) comprising an engaging section (74), wherein the respective engaging sections (70, 74) are engaged to circumferentially and radially fix the rotor disk portion (68) and the blade unit portion (72) relative to each other; a locking plate (96) connected to the rotor disk portion and the blade unit portion such as to axially fix the blade unit portion with respect to the rotor disk portion, wherein the locking plate (96) is axially spaced apart by a spacing (D) from an axial end (98) of the engaging portions (70, 74) of the rotor disk portion (68) and/or the blade unit portion (70) leaving a void region (V) axially between the engaging portions (70, 74) and the locking plate (96). |
