GB719801A - Means for supplying liquid fuel to prime movers - Google Patents

Abstract

719,801. Jet propulsion engines; gas turbine plant. LUCAS (INDUSTRIES), Ltd., J. Jan. 22. 1953 [Feb. 13, 1952], No. 3788/52. Class 110(3) [Also in Groups XI and XXXV] A gas turbine or jet propulsion engine fuel system comprising a fuel pump which delivers fuel to the burners through a main path and a by-pass path arranged in parallel with a portion of the main path, a volume control in the main path and means responsive to a pressure difference in the main path for controlling the flow in the by-pass path has a connection between the by-pass path and the sump or inlet of the pump and electromagnetic means responsive to a temperature of the engine for actuating two valves one of which closes the by-pass path and the other diverts fuel from the main path to the sump or inlet of the pump. A variable delivery pump a supplies fuel to the burners b of a gas turbine c through a main path d. The fuel flow in the path d is controlled by means e which acts on a servo-mechanism f which regulates the output of the pump a. The means e may be operated manually or by automatic means responsive to such factors as the speed of the gas turbine, atmospheric pressure or the air pressure supplied by a blower. A by-pass path h connects the discharge of the pump a to the outlet of the control means e. The flow through this by-pass is controlled by a closure member n mounted on a flexible diaphragm m, the movements of which are controlled by the pressure drop across a restriction g in the main path. An electromagnetically operated valve p is arranged in the by-pass path h and a similar valve q controls the flow into the passage r leading to a sump or the inlet side of the pump a. The electromagnet s for operating the valve p has a pair of opposed windings v, w and the electromagnet t has a single winding x. The windings w, x are connected in series and are energized by electronic or other apparatus u controlled by a thermocouple y in the jet pipe, combustion chamber or other part of the gas turbine c. When the engine is started, the winding v is energized and the valve p opened. Fuel then flows through the main and by-pass paths to the engine. When the temperature in the vicinity of the thermocouple exceeds a predetermined amount the electromagnet v is neutralized by the electromagnet w and the valve p closed by the spring 2. Should the temperature continue to increase, the valve q is opened and fuel is diverted from the main path through the by-pass paths to the sump or inlet of the pump. The valves p and q may, if desired, be actuated simultaneously.