Improvements relating to rotary fluid-flow machines

1,061,479. Gas turbine plant, axial-flow compressors. DAIMLER-BENZ A. G. June 24, 1964, No.26172/64. Headings F1C, F1G and F1T. A turbine has a hollow shaft which is connected at both its ends with radial struts extending from the walls of the turbine housing by releasable means adapted to carry axially outer bearings for two adjacent rotors, and carries at its axial centre a part T-shaped in axial cross-section arranged between axially inner bearings for the rotors. In a gas turbine engine the rotors 14, 15 each have a set of compressor blades surrounded by a set of turbine blades, and are mounted in bearings 12, 13, 26, 27. A hollow shaft 11 rigidly connected at its ends 17, 18 to support struts 51, 52 by parts 19 to 21 and 22 to 25, carries the rotor bearings 12, 13 in a part 16 integral with or secured to the central portion thereof. The parts 19 to 21 support the bearing 26 and the parts 22 to 25 support the bearing 27 and gearwheels 28 of a gear train 29. The gear train interconnects the rotor 15 with a drive shaft 30 for auxiliaries, such as lubricant pumps 31, 31' and a centrifuge 32 incorporated in a lubrication system substantially the same as the one described in Specification 1, 061, 478. A passage 46 in the part 16 conveys sealing air 48 from the hollow shaft 11 through a passage 47 to labyrinth packings 45. A partition 41 between the rotors 14, 15 forms a chamber 43 to which compressed air is supplied to balance the axial thrust set up by the turbine and compressor. The turbine may be vertically arranged in an aircraft.