| 摘要 |
<p>The invention is directed to a gas turbine engine (1) comprising a rotor, the rotor comprising a stud (10), a first set of rotating elements (20, 21) of a first section (2), particularly a compressor section, of the gas turbine engine (1), and a second set of rotating elements (30, 31) of a second section (3), particularly a turbine section, of the gas turbine engine (1), the first and second set of rotating elements (20, 21, 30, 31) particularly being discs (20, 30) and/or shafts (21, 31). The stud (10, 11) is extending along an axis (A) and comprising a first external end (12) and a second external end (13), the first external end (12) adapted to engage a first pre-load nut (40) or one of the shafts (21) and the second external end (13) adapted to engage a second pre-load nut (41) or one of the shafts (31) such that the set of rotating elements (20, 21, 30, 31) are secured, a first shank (15) connected to the first external end (12) and a second shank (16) connected to the second external end (13). The first shank (15) is located in the first section (2) and has a first diameter (D1) which is preferably adapted for temperatures occurring in the first section (2) during operation of the gas turbine engine (1). The second shank (16) is located in the second section (3) and has a second diameter (D2) greater than the first diameter (D1), the second diameter (D2) preferably being adapted for temperatures occurring in the second section (3) during operation of the gas turbine engine (1). In a preferred embodiment the first shank (15A) is tapered such that the first diameter (D1) increases in axial direction.</p> |
