GB620721A - Improvements in gas turbine unit for the propelling of aircraft and other vehicles - Google Patents

Abstract

620,721. Gas turbine plant. SVENSKA TURBINFABRIKS AKTIEBOLAGET LJUNGSTROM. Oct. 14, 1946, No. 30583. Convention date, Oct. 13, 1945. [Class 110(iii)) ] In a gas turbine plant comprising three turbine rotors 3, 4, 5 driving respectively a compressor 1 and airscrews 21, 27, the rotors 4, 5 rotate in opposite directions within a common bladed stator 35 which is free to rotate so as to equalize the torques of the rotors 4, 5. The Specification as open to inspection under Sect. 91 comprises also the following: In a tractor arrangement the propeller shafts pass through the tubular compressor shaft. In a pusher arrangement the turbine exhaust is carried, by a radial pipe, outside the sweep of the propeller blades. The stage speeds may be arranged so that no reduction gear is needed. When the stages comprise single rings of impulse bladings, reduction gears are provided in the propeller drives. Reduction gears are also provided for lifting propellers of helicopters. Two propellers may be driven by the two rotors of a contra-rotating stage. In the form shown in Fig. 5 (Cancelled), the compressor is driven by the inner rotor 3 and a propeller 21 is carried by the outer contra-rotating rotor 4. A second propeller 27 is carried by an outer rotor 5 of a turbine the inner element of which is stationary. In Fig. 6 (Cancelled), the compressor is driven by the stage rotor 3 and the propellers 21, 27 are driven by the contra-rotating rotors 4, 5. This subject-matter does not appear in the Specification as accepted.