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UnitedStatesPatentO??ce 1 3,374,622 Patented Mar. 26, 1968 2 3,374,622 FUEL SYSTEMS FOR GAS TURBINE ENGINES Thomas Charles Yates, Solihull,‘England, assignor to Joseph Lucas (Industries) Limited, Birmingham, England Filed June 9, 1966, Ser. No. 556,442 2 Claims. (Cl. 60-3928) ABSTRACT OF THE DISCLOSURE A fuel system for a gas turbine engine having a throt tle arranged on the downstream side of a fuel pump and 'an engine speed reponsive governor for protecting the engine from overspeeding by limiting the amount of fuel delivered. A main manually operable power means for varying the throttle setting and an auxiliary manually operable power means ‘for varying the throttle setting due to failure of the main power means are provided. Also included are means energized when the auxiliary power permit How of fuel from the supply pipe 15 through the restriction 20 to the pump inlet. This valve 21 is operated by an engine speed responsive governor 22 which, in this example is of the ?y-weight type, and has springs 23a and 23b, the loading of which determine the engine speed at which the valve 21 opens, with the valve and governor being rotatable by the engine 12 through suit gearing indicated by numeral 24. The system also includes main power means for vary ing the setting of the throttle 14, comprising a man ually operable selector 25 for energizing an automatic electronic control 26 incorporating means responsive to the various functions which dictate safe engine control duringacceleration,decelerationandsteadyrunningcon ditions of the engine. The main power means also in cludes an alternating current electric motor 27 which is connected to the throttle 14. The system further includes an auxiliary power means in the form of a direct current electric motor 28 which means is energized and responsive to changes in the 20 can be run at a slow speed under the direct control of the aircraft pilot through a button 29. This motor 28 cannot be run at a speed which will induce stalling of the engine due to excess fuelling. The auxiliary power means for setting the throttle 14 is part of an emergency stand-by system in an aircraft, for use in the event of the failure of the main power means and is supplied from a separate power source (not shown). The two motors 27 and 28 are capable of moving the throttle 14 throttle setting and arranged to modify the response of the governor to engine speed. This invention relates to fuel systems for gas turbine engines and of the kind comprising a fuel pump which is capable of delivering fuel to the engine through a throttle, an engine-speed responsive governor for pro tecting the engine against overspeeding by limiting the quantityoffueldeliveredthereto,amainmanuallyoper 30 agemechanism30oralternativelythroughadifferential able power means for varying the setting of the throttle in accordance with certain predetermined requirements, and an auxiliary manually operable power means also for varying the setting of the throttle, with said auxiliary power means being intended for use in the event of fail ure of the main power means. The object of the present invention is to provide a fuel system of the kind speci?ed, in a convenient form. gearbox. For use only when the auxiliary power means is ener gized, there is provided apparatus comprising a device 31 which in this example, is a variable inductance but may alternatively be a variable capacitance, which senses changes in the setting of the throttle 14 and generates an electrical signal which is fed to an electrical control unit 32 arranged to energize an electric motor 33 which, in turn varies the position of a cam 34 which engages a According to the present invention, a fuel system of the kind speci?ed is characterized by the provision of 40 movable abutment 35 for the spring 23a of the gov apparatus energized when the auxiliary power means is energized, and ‘being responsive to changes in the throttle setting to modify the response of the governor to engine speed. A speci?cexampleoftheinventionwillnowbede scribed with reference to the accompanying drawing which is a diagrammatic representation of a fuel system for a gas turbine engine for installation in an aircraft. ernor 22. With this arrangement, changes in the throttle setting are used to vary the response of the governor 22 to en gine speed and thus the speed at which the valve 21 will opentopermitspil.Itwillbeappreciatedthatnormal ly, when the main power means is in operation, the gov ernor 22 acts as a topspeed governor only, but when the auxiliary power means is in use, the governor 22 re Inthisexamplethefuelsystemcomprisesavariable. sponseismodi?edtominimizetheriskofoverspeeding stroke swash-plate type pump 10 for delivering fuel to burners 11 in an engine 12, the fuel being supplied from a tank 13. There is a throttle 14 disposed in supply pipe 15 between the pump 10 and the burners 11, and the stroke of the pump 10 is controlled by a piston and cyl inder type servo mechanism 16 one end of which is sub jected to pump inlet pressure and this end also con taining a spring, and the other end of the mechanism 16 is subjected to the pressure at the downstream side of the pump as modi?ed by a valve 18, through a pipe 19. at throttle settings below the maximum as well as at the maximum speed of the engine. When the auxiliary power means is in operation due to failure of the main power means, or for any other reason, the pilot can thus select any fuel ?ow rate as may be required under varying conditions. At a point during throttle movement, the engine speed ceases to be determined solely by the ?ow permitted by the throttle and is determined at least in part by the governor 22. The engine speed at which this ‘occurs is dependent upon aircraft speed, altitude, and climatic con ditions.Inmostinstancestheupper10% ofthespeed rangeoftheengineissubjecttocontrolbythegovernor 22, this being the range over which, most of the time, an aircraft engine is run. Thus speed selection over this This valve 18 per se is responsive to changes in the pressuredropacrossthethrottle14.Fuelinthepipe19 canalsoreachtheinletofthepump 10throughare striction 20. With this arrangement, should the quantity of fuel delivered by the pump exceed that which can pass the throttle 14, the excess fuel will be spilled through the valve 18 and will also exert a pressure on theservomechanism14toreducethepump strokeuntil the correct quantity of fuel is being delivered to the en gine.Thepumpstrokeislikewiseincreasedifthequan 70ormodi?cationsmaybemadethereinsolongassuch tity of fuel being delivered is inadequate. The system also has a ‘further valve 21 which can also changesormodi?cationsmarknomaterialdeparturefrom ‘ the spirit and scope of the appended claims. independently and the drive takes place through a lever range is by the pilot’s button 29 but the governor 22 ensuresthattheselectedspeedismaintainedsubstantially constant.Theinventionisnottobecon?nedtoanystrict conformity to the showings in the drawings but changesPDF Image | FUEL SYSTEMS FOR GAS TURBINE ENGINES
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