GB720436A - Improvements in gas turbines, especially for vehicles - Google Patents

Abstract

720,436. Gas turbine plant. KOVATS DE KEZDIVASARHELY, A. DE. Aug. 7, 1952 [Aug. 8, 1951], No. 19962/52. Class 110 (3). In a gas turbine plant for vehicles comprising a turbine driving a compressor, a useful-power turbine, a combustion chamber and a heat exchanger for transmitting exhaust gas heat to the compressed air, the rotor of the useful-power turbine turns in the opposite direction to the rotor driving the compressor and is fed by a volute having no guide blades. The gas turbine plant comprises a low-pressure turbinecompressor unit 42, 47, a high-pressure turbine unit 2, 7 which includes the useful power turbine 6 and combustion chambers 4, 44 arranged as shown. When the high-pressure unit is on no load a valve 46 is actuated to divert the air supplied by the compressor 42 directly into the combustion chamber 44. An oil pump 12, a fuel pump 13 and a starting motor 11 are geared to the low-pressure unit 42, 47. In a modification, the auxiliaries 11, 12, 13 are geared to the unit 2, 7 and the unit 42, 47 is dispensed with. As shown in Fig. 4, the rotor 7 is mounted on the hub of the compressor 2 and drives the auxiliaries through a shaft 8 disposed within a fixed shaft 18. Oil is fed through a conduit 16 and the shaft 18 into the space between the said shaft and the hub of the rotor 2 and after lubricating the bearings it is discharged through a passage 17. Cooling air is fed into the space between the rotors 6, 7 through ports 20 in the rotor 7 whilst additional cooling air is fed into the turbine casing through a conduit 21 and is discharged therefrom through ports 23 communicating with the turbine inlet volute. In a further modification, the compressor 2 withdraws air' from an annular space surrounding the hub of the compressor rotor and the ports 20 are dispensed with. The compressor 2 may constitute a multi-stage compressor or be of the axial-flow type.