Patent GB-1071241-A (GB)
Title: Fuel flow apparatus for combustion engines
IPC: F02K1/17
Filed: 1964-08-05
Abstract: 1,071,241. Gas turbine engine fuel systems. BENDIX CORPORATION. Aug. 5, 1964 [Sept. 13, 1963], No. 31843/64. Headings F1G and F1J. [Also in Division G3] A fuel control system for controlling flow of fuel to the main combustion equipment of a gas turbine jet engine comprises a variable area fuel metering valve 84, 81 which is operatively connected to actuating means the position of which is controlled on one hand by a first follower 106 which is operative to engage a first three dimensional cam 99 which is movable rotationally in dependence on engine compressor speed sensed by the centrifugal governor device 164 and axially in dependence on compressor inlet temperature which acts on bellows 190, and on the other hand by a second follower 128 which is operative to engage a second three dimensional cam 132 which is moved rotationally by the engine control lever 54 and axially by means of a lever 258, the position of the lever 258 being controlled by a third follower either 269 or 260 which are operative to engage either third three dimensional cam 233 or 234 respectively, the cams 233 and 234 being moved rotationally in dependence on compressor inlet temperature as effective on bellows 190, and axially in dependence on compressor inlet pressure which is effective on bellows 248 Fig. 3. The question as to which of the cams 233, 234 is effective at any one time is dependent on the position of the control lever 54; in the non-reheat position of the lever the space 261 above the. piston 262 is connected to drain pressure so that the piston 262 and roller 272 are biased by the spring 274 to the right and the spring 271 causes the lever 268 to pivot clockwise so that the follower 269 is biased away from the cam 233, and the spring 266' pivots the casing 260 about its pivotal point 263 and thus the follower 270 bears against the cam 234, movement of the follower 270 pivoting the casing 260 whereby the lever 258 moves the cam 132 in an axial direction. The engine is shown diagrammatically in Fig. 1 and comprises a fan 28, a low pressure compressor 29 and a high pressure compressor 32, combustion equipment 35, a high pressure turbine 33 which drives the high pressure compressor 32 through shaft 34, and a low pressure turbine 30 which drives the low pressure compressor 29 and fan 28 through shaft 31. The main combustion equipment 35 is supplied with fuel through line 44 from the main fuel control 43. The engine comprises also reheat combustion equipment comprising fuel manifolds 38, 39, 40 which are supplied with fuel through lines 56, 57, 58 from reheat fuel control 55. The engine comprises also a variable area nozzle comprising flaps 27 movable by means of a piston and cylinder device 64, 65, the operating fluid of which is supplied through lines 66, 68 from the nozzle control 70. The position of the flap members 27 is fed back to the control 70 by means of a link 75 and pulley 74. The main fuel control is supplied with fuel through inlet 45 from tank 46 through pump 47 and the interior of the control unit is connected to the pump inlet through line 53. The main fuel control is supplied with signals indicative of air intake pressure and temperature P 1  and T 1  from pick-ups 49 and 50. The speed N 2  of the high pressure compressor 32 is transmitted to the control unit through the linkage indicated at 51. High pressure compressor discharge pressure P c  is transmitted to the control unit through line 52. The throttle lever 54 is also connected to the main control unit. The main control unit is shown in Figs. 2 and 3, the fuel inlet 45 and fuel outlet 44 being shown in Fig. 3 as is also the metering valve 84, fuel passing from inlet 45 through line 78 containing filters 79, 80, through the variable area orifice 81 controlled by the metering valve 84 and then through the spring-loaded valve 82 to the discharge line 44 to the main fuel burners 36. The position of the metering valve 84 is controlled by means of a servo-piston 87 formed integrally therewith, the piston having a restricted orifice 92 formed therein. Fuel at pressure P R  is supplied to the lower side of the piston through line 90 and the fuel above the piston discharges through line 93 to the interior of the casing, the outlet 94 of the line being controlled by a vent valve pivotally mounted at 200. The position of the metering valve 84 is regulated as a function of speed N 2  of the high pressure compressor by a governor and acceleration cam 98, 99 Fig. 2. A second cam 100, 101 is secured to the cam 98, 99, the two cams being mounted for axial movement on a shaft 102 and are rotatable therewith, the pinion 103 of the shaft being engaged by a rack 104 which is integral with a servo-piston 105. A follower 106 is urged into contact with the cam portion 99 by spring 110, a lever 107 being pivotally connected at one end to the follower and at the other end to the rod of a servo-piston 109. A cam follower 113 is urged into engagement with cam portion 98 by lever 114 pivotally connected at one end to follower 113, the lever being urged anticlockwise by spring 115. The upper end of the lever 114 engages a ball servo-valve 116 which co-operates with a valve seat 117 forming part of the servo-piston 109. Fuel at pressure P R  is supplied to the right-hand side of piston 109, fuel at pressure P s  at the left-hand side of the piston leading off through duct 118 under control of the ball valve 116. A speed request cam 132 is slidably mounted on a shaft 133 and is rotatable therewith in response to movement of throttle lever 54. The rod 131 is movable between an engine idle speed adjustment including a stop 136 and a stop 139 the position of which is controlled by a piston 144 acted on at its lower side by regulated fuel pressure P R  and at its upper side by drain pressure P o  and by spring 146. Servopiston 105 which actuates rack 104 is acted on at its right hand face by fuel at pressure P R , the fuel passing through restricted passage 155 in piston 105 and discharging through line 156, the outlet 157 of which is controlled by the vent valve 158 as a function of high pressure compressor speed N 2 . The lever 158 is acted on by member 159 the axial position of which is controlled by the centrifugal governor device 164. The force applied to the lever 158 by the bearing member 159 is opposed by a constant reference force derived by spring 165 and communicated to the lever through a roller 167 which rolls between the lever and a spring plate. The opposite end of the spring is controlled by temperature responsive discs 169, the discs being responsive to temperature of the surrounding fuel. The roller 167 is connected to a lever 172, the opposite end of the lever having a follower 173 pivotally connected thereto, the follower 173 bearing against the cam portion 100. The governor and acceleration cam and second cam secured thereto are actuated axially on the shaft 102 as a function of compressor inlet air temperature T 1  by means of piston 175 integral with rack 176 having a retaining annulus 177. A lever 178 engages at one end annulus 177 and at its other end annulus 179 formed on the second cam. The servo-piston 175 is acted on at its upper face by regulated pressure P R  and at its lower face by pressure P s , the leak-off from the lower side of the piston through line 183 and vent 184 being controlled by valve 185 pivotally mounted at its right-hand end on the rod of piston 175 and acted on at its left-hand end by one arm of a bell-crank lever 186 which is controlled by the bellows 190 in dependence on compressor intake temperature T 1 . The cam follower 106 is connected to a yoke 198, Fig. 3 which carries a roller 199, the roller 199 rolling between one arm of a bell-crank lever 200 and a cross-arm 201 of T-shaped lever 202 which is pivotally secured to the casing. The opposite end of the lever 202 is connected to a bellows 203 which is responsive to compressor discharge pressure P c  supplied to the chamber 205 through passage 206. The load applied to the lever 200 by the roller 199 is opposed by a spring 207 interposed between spring retainers 208, 209, the retainer 208 bearing on the lever 200 through a roller 199' and the retainer 209 acts on temperature compensating discs 210. The roller 199' is carried on a yoke connected to the metering valve 84. The device 213 acts to limit compressor discharge pressure P c  to a predetermined maximum value. Fuel at regulated servo pressure P R  is delivered to variable area nozzle control 70 through passage 226, Fig. 2, the passage 226 communicating with passage 181 and with valve 227 and line 228. At a predetermined position of the servo-piston 105 which corresponds to a predetermined high pressure air compressor speed N 2 , the arm 232 connected to the piston rod, acts against lever 230 to cause the slide valve 227 to open whereby passage 226 is connected to line 228 and fuel at regulated servopressure P R  is communicated to the variable area nozzle control. The speed request cam 132 is moved axially on shaft 133 as a function of compressor inlet air temperature T 1  and pressure P 1  by either of two cams 233 or 234 fixedly secured together and slidably carried on shaft 235 which is rotatable by the servo-piston 175 through a rack and pinion 176, 236. The cams are moved axially by means of the servo-piston 240 acting through follower 237. Servo-fluid supplied from line 181 passes through passage 242 to the right-hand side of piston 240 then passes through restriction 243 in the piston to the left-hand side of the piston and then discharges through line 244 and outlet 245 to the interior of the casing, the outlet 245 being controlled by one arm 254 of the bell-crank lever, Fig. 3. The other arm of the lever is controlled by a bellows 248 disposed in a chamber 247 to which compressor air inlet pressure P 1  is communicated. The horizontal arm 254 of the lever is loaded by a constant refere