GB765107A - Fuel supply system for a gas turbine engine power plant - Google Patents

Abstract

765,107. Gas turbine plant. ROVER CO., Ltd. May 5, 1955 [May 11, 1954], No. 13681/54. Class 110 (3). In a gas turbine engine fuel system comprising an engine-driven pump having a constant output characteristic delivering fuel to a burner having means for varying its nozzle area in accordance with its rate of fuel supply, a by-pass leading from between the pump outlet and burner inlet has means for diverting from the burner, a proportion of the pump output which is varied by maximum and minimum engine speed control means and an accelerator. A constant output pump 10, which is of the swash-plate type and is driven from the turbine-compressor shaft 13 through reduction gearing 11, 12, draws fuel from the reservoir 16 and delivers it to the burner 17. The burner 17 is of a known type in which a piston 18 is movable against a bias by the fuel pressure in a cylinder 19 to position a valve member which varies the effective area of the nozzle. The area of the nozzle increases with increase of fuel supply and vice versa. A bypass 20 extends between the pump outlet and inlet and the flow through it is controlled by three valves 23, 24, 25. Valves 24, 25 are actuated by speed-responsive governors 26, 27 driven from the shaft 13. The governor 26 is the minimum speed and the governor 27 the maximum speed governor. The valve 23 is the manually-operated accelerator valve. Under idling conditions, the valves 23 are fully open. If the valve 23 is moved in the closing direction the fuel supply to the burners is increased and the engine accelerates. If this causes the engine to overspeed, the valve 25 opens to by-pass fuel around the valve 23.