Patent ID: 7470110

Claim:
A turbine or compressor device comprising: a rotor ( 1 ) including a first rotor section ( 2 ) having at least one disc-shaped or annular element ( 3 ) which has a multiplicity of blades ( 4 ) arranged in series on a circumferential path for guiding a gas flow, and a second, elongate rotor section ( 5 ), which projects at right-angles from the rotor disc ( 3 ) and which comprises a rotor shaft ( 6 ) connected to the rotor disc; a first and second bearing ( 8 , 9 ) fitted at a distance from one another along the rotor shaft ( 6 ), the first bearing ( 8 ) being arranged closer to the rotor disc ( 3 ) than the second bearing ( 9 ) and wherein a bearing holder ( 25 ) of the first bearing ( 8 ) has a greater outside width than other components ( 9 , 14 , 15 , 31 ) arranged on the rotor shaft ( 6 ) between the first bearing ( 8 ) and a free end of the rotor shaft ( 7 ); and a stator ( 26 ) comprising a series of blades or vanes and having a first stator housing part ( 11 ) arranged in a position proximate to the rotor disc ( 3 ), the first stator housing part being configured to be placed and fixed in position in a direction away from the free end ( 7 ) of the rotor shaft ( 6 ).