GB717590A - Improvements in and relating to liquid fuel supply systems for aircraft gas turbine engines - Google Patents

Abstract

717,590. Gas turbine plant. DOWTY EQUIPMENT, Ltd., and SIMMONS, H. C. Oct. 10, 1952 [Oct. 11, 1951], No. 23733/51. Class 110(3) [Also in Group XI] In a gas turbine fuel system comprising two pumps, one of which, a circulating pump, circulates fuel around a circuit including the swirl chambers of spill type burners and the other, a supply pump, supplies controlled quantities of fuel to the circuit, the circuit comprises a plurality of spill burners 15 each having an inlet connected through a non-return valve 23 to a common burner ring 13 and a spill orifice connected through a non-return valve 25 to a common collector ring 17, an engine driven centrifugal or other non-positivedisplacement type pump 11 having its inlet connected to the collector ring and its outlet to the burner ring through a shut off cock 24 and a branch line connected to the supply pump. The non-return valves 23, 25 may be incorporated in the burners. The engine driven supply pump 19 injects fuel from the supply tank 20 into the circuit at the inlet of the circulating pump 11. The rate at which fuel is injected is regulated by a manually operated unit 21 and by-pass valve 22. A diversion cock 27 may be used to direct fuel from the pump 19 either to the circuit or to a by-pass 28 leading back to the suction of the pump 19. The cocks 24, 27 may be ganged together so that when cock 24 is closed, cock 27 diverts the fuel back to the suction of the pump. The cock 27 may be included in the circulating pump circuit in which case the circuit will have two connections with the supply, one with the delivery of the pump 19 and one with the return passage 28. If the pump 11 fails, the valves 25. will close and the burners will then operate as direct injection nozzles. The supply pump system may include controls responsive to engine speed, ambient air conditions and acceleration.