GB602554A - Improved means for regulating internal combustion turbine plants - Google Patents

Abstract

602,554. Gas turbine plant. AKT.-GES. BROWN, BOVERI, & CIE. Oct. 17, 1945, No. 27165. Convention date, Nov. 10, 1944. [Classes 110 (i) and 110 (iii)] In a gas turbine plant comprising at least two compressor-turbine sets on separate shafts, the compressors and turbines being in series and one compressor-turbine set providing useful power, the fuel supply to the combustion chamber preceding the turbine providing useful power is regulated directly from the power regulator and the fuel supply to the other combustion chamber or chambers is regulated directly or indirectly from the same regulator. In the plant shown in Fig. 3, the high-pressure set 3, 5 drives a useful power generator 8 and the fuel supply to the combustion chamber 4 is regulated directly from the governor 10. The fuel supply to the combustion chamber 6 is regulated by the governor 11 on the lowpressure set but the setting of that governor is regulated by the governor 10. The servomotor 13 operating the fuel supply means to chamber 4 has an over-riding limit control from a thermostat 15. A limit control on the low-pressure set is provided by a thermostat 14 which controls a byepass 16 across the lowpressure set. In another plant, the lowpressure set provides the useful power and its governor controls the separate fuel supplies to the combustion chambers before both high and low pressure turbines. The governor on the high-pressure set has a limit control over the fuel supply to the high-pressure combustion chamber and there is a device in the control pressure fluid line to prevent this latter governor affecting the servomotor controlling the fuel supply to the low pressure combustion chamber. In a variation of this plant, the direct control of the fuel supply to the high pressure combustion chamber by the speed governor of the low-pressure, useful power set is omitted and that fuel supply is controlled only by a speed governor on the high-pressure set. Alternatives to the limit control 14, 16, Fig. 3, are described. In one, power is transferred from the high-pressure to the low-pressure set shaft by means of a motor in place of the starting motor 9 which is regulated from the thermostat 14. In another, the low-pressure turbine 7 is provided with a ring of initial guide blades the angular position of which is controlled from the thermostat 14. These blades are radial flow blades in front of the normal axial inlet to the axial flow blading. In a third, a stand-by high-pressure stage is provided in the turbine 7 which can be put in parallel with the normal high-pressure portion of that turbine by means of the thermostat 14. In a fourth, the highpressure compressor 3 has an initial ring of angularly-adjustable guide blades, the positions of which are controlled by the thermostat 14.