GB904621A - Improvements relating to the rotors of flow machines - Google Patents

Abstract

904,621. Turbine and compressor rotors. DAIMLER-BENZ A.G. April 6, 1961 [April 9, 1960]. No. 12446/61. Class 110 (3). In a rotor for a flow machine, such as a turbine or compressor, having a number of rotors mounted so as to be separately rotatable, hub ports which project beyond the width of the annular rotor disc and have radially outwardly-facing centring surfaces or seatings for bearings at their outer ends are so constructed, arranged or connected to the disc as to act as expansion-permitting parts by which operational temperature and centrifugal force stresses are attenuated axially outwards. The rotor hub part 12, Fig. 1, extends axially in opposite directions to form outer parts 12<SP>1</SP> and 1211, each constricted by expansion necks formed by channels adjoining the rotor disc 11. Seating rings may, as shown, be interposed between the hub parts 12<SP>1</SP>, 12<SP>11</SP> and the inner races of bearings 16, 17. Abutment surfaces 19 bear against the inner races or seating rings. Compressor blades 23 and gas-turbine blades 24 are provided. Fig. la shows an alternative mounting wherein a split seating ring 20 locates the rotor axially by means of shoulders 21, a flange 22 being bent into position 221 to secure the ring to the inner race of bearing 16. In another embodiment, dished side parts 113, 114, Fig. 2, which may be of steel, are secured at positions 113<SP>1</SP>, 114<SP>1</SP> to disc 111 which may be of light metal.