Fuel Flow Control Apparatus for Gas Turbine Engines.
Номер патента: GB1171781A
Опубликовано: 26-11-1969
Автор(ы): Owen Napier Lawrence
Принадлежит: Joseph Lucas Industries Ltd, Lucas Industries Ltd
Опубликовано: 26-11-1969
Автор(ы): Owen Napier Lawrence
Принадлежит: Joseph Lucas Industries Ltd, Lucas Industries Ltd
Реферат: 1,171,781. Gas turbine engine fuel systems. JOSEPH LUCAS (INDUSTRIES) Ltd. Feb.16, 1967 [Jan.6, 1966], No.595/66. Heading F1G. [Also in Division G3] Apparatus for controlling the supply of fuel to a gas turbine engine comprises a pump 10, an axially movable throttle 17 for controlling delivery from the pump, means 22 controlling the output of the pump to maintain a constant pressure drop across the throttle being connected to a piston 34 in a cylinder 35 to one end of which fuel is supplied from the upstream side of the throttle, a manually operable plunger 40 movable coaxially within the piston to control the escape of fuel from said one end of the cylinder, a passage 47, 48 connecting opposite sides of the means 22 through a restriction 49, 50, 51 which is varied when the plunger 40 is moved beyond a predetermined limit at a rate greater than the rate of travel of the piston so that the means 22 causes the pump to restore the constant pressure drop across the throttle. Cam portions 44, 45 on the plunger and piston cause the plunger to be rotated and the restriction to be reduced when the predetermined rate is exceeded. A cam 52 connected with a tubular extension 33 of the piston 34 is engaged by a roller 53 to give the throttle an initial angular movement which is dependent on the speed of the engine. The travel of the plunger 40 before the cam portions 44, 45 engage is also therefore dependent on the speed of the engine. An orifice 38 in the extension 33 forms a moving-seat follow-up with passages 39, 41 in the plunger. To control the output of the pump 10 a servopiston 12 is controlled by a bleed-off valve 24 on a lever 23 actuated by a capsule assembly 32 responsive to pressure in the engine compressor and by the diaphragm 22 which is subjected to the pressure drop across the throttle 17 modified by a temperature signal from the engine applied to a solenoid valve 29 through an electrical control 27. The supply to the burners 16 is also controlled by a pressurizing valve 19 and a shutoff cock 20.
Speed-adjustable automatic fuel-control apparatus for internal- combustion turbine engines
Номер патента: GB1413882A. Автор: . Владелец: Plessey Co Ltd. Дата публикации: 1975-11-12.