US3760590A - Device for metering ignition fuel to the ignition unit of an afterburner associated with a turbojet engine - Google Patents

Device for metering ignition fuel to the ignition unit of an afterburner associated with a turbojet engine Download PDF

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Publication number
US3760590A
US3760590A US00131713A US13171371A US3760590A US 3760590 A US3760590 A US 3760590A US 00131713 A US00131713 A US 00131713A US 13171371 A US13171371 A US 13171371A US 3760590 A US3760590 A US 3760590A
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Prior art keywords
fuel
control
cylinder
ignition
piston
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Expired - Lifetime
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US00131713A
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English (en)
Inventor
E Bader
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MTU Aero Engines GmbH
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MTU Motoren und Turbinen Union Muenchen GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners

Definitions

  • This invention relates to a device for metering the ignition fuel to the ignition unit of an afterburner associated with a turbojet engine with a first cylinder chamber for charging and discharging as well as for storing of the ignition fuel, for which purpose a control spool or piston axially movable against the force of a return spring is arranged in this first cylinder chamber, and with a second cylinder chamber adjacent to the first cylinder chamber and including a second control spool or piston, which is actuated by an external source and axially movable against the force of a return spring.
  • This second control spool either releases the H.P. (high-pressure) fuel supply initiating the discharge motion of the first control spool by simultaneously shutting off the LP. (low-pressure) fuel supply or cuts off the H.P. fuel supply for the recharging motion of the first control spool with a simultaneous opening of the LP. fuel supply.
  • H.P. high-pressure
  • LP. low-pressure
  • A' device for metering the ignition fuel which essentially-features thecharacteristics of the device as described hereinabove, is known from the German Patent 1,284,158.
  • the invention is to solve the following problem:
  • the pressure of the fed H.P. fuel supply is the controlling parameter for the discharge time of the first control spool forcing the ignition fuel out of the device, when operating at high altitude the discharge time for the ignition fuel must be expected to be considerably longer than under operation at low altitude.
  • such means could be constituted by pressure relief valves adjusted to suit the varying H.P. fuel pressures.
  • valves could be arranged inside of the wall of the first cylinder chamber; however," they could also be arranged outside the first cylinder chamber, e.g., in pipes through which the excess fuel is returned to the fuel tank.
  • valves could thus all be closed simultaneously if, for example, a specified minimum pressure of the H.P. fuel is not maintained, i.e., exceeded during the operation of the aircraft at low altitudes in order to prevent in this manner too rapid a discharge and an injection by the first control spool.
  • all valves could be in the open position if a minimum pressure of the H.P. fuel is established during discharge motion of the first control spool, which is smaller than the spring pretension of the pressure relief valves.
  • These valves can be so arranged and designed that they ensure essentially the same rapid light-off or ignition of the afterburner under any operating condition as a function of the pressure of the H.P. fuel increasing or decreasing with higher or lower flight altitudes in a linear manner.
  • an actuating spool or piston which is axially movable in a cylinder can be provided which, on one end, is loaded by a spring arranged in this cylinder, while the other end extending into the first cylindrical chamber of the device is subjected to the discharge fuel pressure; this other end is equipped with a contact pin pointing towards the inner surface of the first control spool which, upon contacting the first control spool, releases an electrical shut-off signal to the second control spool constructed as a solenoid valve.
  • Thisactuating spool limits the injection time and the ignition fuel quantity as a function of the pressure differential between the pre-loaded spring and the injection fuel.
  • FIG. 1 is a longitudinal cross-sectional view of a device for metering the ignition fuel, according to the invention, with a schematic cut-away side view of a turbojet engine, including a fuel supply system of the engine and its associated afterburner.
  • FIG. 2 is a longitudinal cross-sectional view of a device for metering the ignition fuel, according to the invention, in a second embodiment and
  • FIG. 3 is a longitudinal cross-sectional view of a third embodiment of a device for metering the ignition fuel according to the invention.
  • the turbojet engine 18, schematically shown above this device, essentially consists of a compressor 19, of a combustion section with combustion chambers 20, 21, of which several could be arranged coaxially to the engine longitudinal axis 22, and of a turbine 23 arranged downstream of and adjoining the combustion section.
  • An afterburner jet pipe 24 with a variable thrust or final nozzle 25 at its end is arranged downstream of the turbine 23.
  • a fuel supply system illustrated in simplified form for fuel injectors 26 arranged within the afterburner pipe 24 with flame holders 26' arranged downstream of the injectors, as well as for fuel injectors 27 arranged in the combustion chambers 20, 21.
  • Two fuel pumps 31,32 are connected to a fuel tank 28 for supplying ignition fuel by way of lines 29, 30.
  • Pump 31 serves for the supply with PM. fuel of the device according to the invention, while pump 32 serves for the supply with LP. fuel of the device.
  • the fuel injectors 26 can be supplied with fuel from tank 28 by way of the line 33 and the pump 34.
  • This fuel pump 34 can be operated to start the fuel supply, for example, by means of a lever 35 and a linkage 36, shown schematically only by a full line.
  • the fuel injectors 27 associated with the combustion chambers 20, 21 are supplied with fuel from the tank 28 by way of a fuel line 37 and the fuel pump 38.
  • the fuel pumps 31, 32 must be actuated by means of another lever 39 by way of linkages 40, 41 schematically shown in full lines, in order to supply fuel to the device according to the present invention.
  • a fuel line 42 is connected to the fuel pump 31, which is connected by way of a bore 43 with the second cylinder chamber 5. In the illustrated position, this bore 43 is sealed off by a front spool end piece 44, while the motion of the second control spool 6 caused by the force of the compression spring 7 is fixed by stop ring 45.
  • a line 46 is branched-off at the pump 32. Lines 47 and 48 are connected to line 46, with line 47 leading to the refilling valve 9 and line 48 to a bore 49 in the cylindrical housing 1.
  • the bore 49 opens into the annular groove 50 of this control spool.
  • One or several bores 51 pass through this second control spool or piston 6 within the area of this annular groove 50 and discharge into a bore 52 extending through this second control spool 6 in a longitudinal direction.
  • the solenoid valve is actuated and then the first control spool or piston 3 is actuated against the force of the return spring 4 by the HP.
  • fuel supplied by way of bore 43, cylinder chamber 5 and stop ring 45, and the fuel present in first cylindrical chamber 2 of the device can flow to the ignition fuel injectors 57, S8 arranged in the combustion chambers 20, 21 by way of bore 53, arranged in the housing cover 8, a line 54 connected thereto and by way of the lines 55, 56.
  • an electrical shifting signal is released in the manner which interrupts, for example, the positive circuit by means of a switch 59, thus causing a current coil 60 surrounding the right-hand portion of the cylindrical housing 1 to release the portion 61 of the second control spool 6 constructed as armature under the action of the compression spring 7.
  • the actuating spool or shifting piston 12, its sleeve 13 as well as the cylinder 11 must be insulated against cylindrical housing 1 of the device.
  • actuating spool or shifting piston 12 is subjected to the action of return spring 17.
  • the pressure of the discharge fuel prevailing in cylindrical chamber 2 acts upon the other end of the actuating spool 12; this means that the respective position of this actuating spool or shifting piston 12 is a function of that pressure differential which results from the spring tension, on the one hand, and the pressure of the of the discharge fuel, on the other. If, for example, the pressure of the discharge fuel decreases by a certain amount when the aircraft is operating at high altitude, this would result in a different position of the actuating spool or shifting piston 12.
  • the travel which the first control spool 3 has to traverse for discharging the fuel, and thus the discharge time as well as the ignition fuel quantity, which is to be supplied to the fuel ignition injectors 57, 58 can be controlled as a function of the given altitude.
  • This end of the actuating spool 12 can as well be subjected to the intake pressure of the compressor 19 of the engine 18 (FIG. 1) instead of being subjected to the action of return spring 17.
  • a line 62 can be provided which is connected to cylinder 11 so that the air pressure tapped-off at the compressor intake, in lieu of the force of the spring 17, acts upon the actuating spool 12 by way of a bore in the cylinder 11.
  • FIG. 2 essentially differs from that shown in FIG. 1 in that the cylinder 64 which includes a first control spool or piston 65 axially movable against the action of a return spring 66, is provided with bores 67, 68, 69. Lines 70, 71, 72 are connected to these bores 67, 68, 69 whereby pressure relief valves 73, 74, 75 are arranged in these lines. Lines 70, 71, 72 combine to form a common line 76 leading to the fuel tank 28 shown in FIG. 1.
  • FIG. 2 differes additionally from that of FIG. 1 in that the electromagnetic actuating device shown in FIG. 1 is replaced by a diaphragm 76' actuating the second control spool or piston 79, this diaphragm being subjected to a hydraulic control pressure acting in the direction of the arrow 77.
  • this diaphragm 76 includes a plunger 78 which engages in the second control spool or piston 79.
  • This second control spool or piston 79 arranged in the associated cylindrical chamber 80 is movfrom which a line 86may lead to the fuel injectors 57, 58 of the engine (FIG. 1).
  • the device is connected with the H.P.
  • the connection of the device with the L.P. fuel system is effected by way of the line 88 branched off at the fuel pump 32 (to FIG. 1), this line 88 again branching off into two lines 89, 90.
  • the line 89 is connected for that purpose with the cylindrical chamber 83 by way of the refilling valve 92; the second line branched off from the line 88 leads to bore 93 in the cylinder 64, by means of which the cylindrical chamber 80 can be charged with L.P. fuel with the second control spool or piston 79 in the end position as shown.
  • the diaphragm 76 will be subjected to a pressure acting in the direction of arrow 77, thereby moving the second control spool or piston 79 towards the left against the spring 81.
  • the H.P. fuel can now flow into the cylindrical chamber 80 by way of this bore 94 and another bore 95 extending through the second control spool 79.
  • the fuel can then act upon the surface of the first control spool 65 which is opposite the spring 66 by way of the central bore 82 of the device, causing the spool 65 to move against the action of the return spring 66,,thus allowing ignition fuel to flow to the ignition injectors 57, 58 by way of the bore 84 and the line 86.
  • the second control spool 79 to the left as a function of the pressure acting upon the diaphragm 76, the LP. fuel supply to cylindrical chamber 80 is thereby shut-off by the second control spool 79 sealing the bore 93.
  • valves 73, 74, 75 are adjusted and designed in such a manner that they respond to different H.P. fuel pressures, i.e., during the discharge motion of the first control spool 65.
  • valves 73, 74, 75 can ensure a rapid ignition of the afterburner of as uniform a duration as possible.
  • these valves 73, 74, 75 can also control the amount of ignition fuel to be supplied as a function of time.
  • FIG. 3 essentially differs from that shown in FIG. 1 in that a dropping resistor generally designated by reference numeral is provided, which is controlled by the given altitude, and which consists of a control spool or piston 104 arranged in a cylindrical chamber 102 and axially movable against the action of a return spring 103, whereby the spool or piston 104 is subjected to the compressor intake pressure of the engine 18 (FIG. 1) acting in the direction of arrow 101.
  • the piston rod 105 designed as sliding contact 105' on its left-hand side, protrudes into a guide cylinder 106 mounted on the cylindrical housing 102. With the motion of the control spool 104, the sliding contact 105 can travel over an electrical resistor 107 connected to the positive circuit.
  • the compressor intake or delivery pressure (arrow 101) of the compressor 19 associated with the engine 18 exceeds a predetermined given value, i.e., when an aircraft equipped with a device according to the invention descends from a relatively high altitude to a considerably lower flight altitude, this increase in the compressor intake pressure results in a motion of the control spool or,piston 104 and of the sliding contact 105 to the left and in a simultaneous increase in the resistance of line 108, which line is connected, on the one hand, with the sliding contact 105' and, on the other, with a current coil 110 surrounding a cylindrical guide means 111 of the device according to FIG. 3. This current coil 110 is connected with the negative circuit by way of the line 109.
  • the lefthand section of the piston rod 114 associated with the control spool 112 which is constructed as magnet armature, is pushed into the area of the current coil 1 10, which is subjected to the voltage of the altitudecontrolled dropping resistor 100 by the resultant motion of the first control spool 112 against the action of the return spring 113.
  • the inductive voltage which can be tapped-off at the current coil 110 is fed to an electric control device 116 of conventional construction by way of lines 114', 115.
  • this control Upon deviation from a specified nominal voltage of the current coil 1 l0, and with simultaneous action of the altitude-controlled dropping resistor 100, this control interrupts the power supply by way of lines 1 l7, 1 18 to the current coil 60, thus causing, as already described in connection with FIG. 1, the second control spool or piston 6 in the shown end position under the influence of the compression spring 7 to close the bore 43 by means of the end section 44 and thus cutting off the H.P. fuel supply.
  • the device for metering the ignition fuel including the altitudecontrolled dropping resistor 100 as well as the piston rod 114 designed as magnet armature associated with the control spool 112, and the current coil 110, it is therefore possible, under conditions of high-flight altitude, at low compressor intake pressure (arrow 101) and at low H.P. fuel pressure, to achieve a discharge time of the ignition fuel to ignition injectors 57, 58 (FIG. 1) which does not exceed that time period required for operation at low altitude, so that the turbine 23 associated with engine 18 (FIG. 1) is not endangered.
  • the maximum control stroke of the first control spool 112 will be limited for this purpose, i.e., the discharge motion thereof will be interrupted immediately upon reaching a specified voltage, stored in the electric control 116, which shuts off the power supply to current coil 60 thus causing the second control spool or piston under the influence of the compression spring 7 to close the bore 43 for the H.P. fuel to be supplied.
  • a device for metering ignition fuel to an ignition means of an afterburner associated with a turbojet engine having parameters which vary with changing ambient conditions and the metering including metering parameters of injection time and injection fuel quantity
  • the device having a first cylinder means forming a first chamber for charging and discharging as well as for storing the ignition fuel, said first cylinder means having charging fuel inlet means and discharging fuel outlet means at one end thereof, a first control piston means being axially movable in said first cylinder means and having a discharging motion in a first direction against the action of a first return spring for discharging the fuel in the first chamber to the ignition means of'the afterburner of the engine and having a charging motion in a second direction for the charging of fuel in the first chamber, and a second cylinder means forming a second chamber arranged adjacent to the other end of the first cylinder means and being in fluid communication with the first chamber, a second control piston means in said second cylinder means actuated by an external source and axially
  • a device characterized in that the elastic force acting upon the first portion of the actuating third piston is produced by a spring disposed in said third cylinder for biasing the actuating piston.
  • the first cylinder means having charging fuel inlet means and discharging fuel outlet means at one end thereof, a first control piston means being axially movable in said first cylinder means and having a discharging motion in a first direction against the action of a first return spring for discharging the fuel in the first chamber to the ignition means of the after burner of the engine and having a charging motion in a second direction for the charging of fuel in the first chamber and a second cylinder means forming a second chamber arranged adjacent to the other end of the first cylinder means and being in fluid communication with the first chamber, a second control piston means in said second cylinder means actuated by an external source and axially movable against the action ofa second return spring, the second control piston means including means for either opening a high-pressure fuel supply with simultaneous opening of the low-pressure fuel supply for the charging motion of the first control piston means, characterized in that the second control piston means is a solenoid valve and the external source provides an electrical signal for actuating
  • control means control both the injection time and ignition fuel quantity as a function of the engine parameters.
  • a device for metering ignition fuel to an ignition means of an afterburner associated with a turbojet engine having parameters which vary with changing ambient conditions and the metering including metering parameters of injection time and injection fuel quantity
  • the device having a first cylinder means forming a first chamber for charging and discharging as well as for storing the ignition fuel, the first cylinder means having charging fuel inlet means and discharging fuel outlet means at one end thereof, a first control piston means being axially movable in said first cylinder means and having a discharging motion in a first direction against the action of a first return spring for discharging the fuel in the first chamber to the ignition means of the afterburner of the engine and having a charging motion in a second direction for the charging of fuel in the first chamber, and a second cylinder means forming a second chamber arranged adjacent to the one end of the first cylinder means and being in fluid communication with the first chamber, a second control piston means in said second cylinder means actuated by an external source and axially mov
  • control means includes a third cylinder means adjacent the first cylinder means and third piston means arranged for axial movement therein the third piston means having a portion thereof arranged within the first chamber and being responsive to the discharging motion of the first control piston means for moving within the third cylinder means, the control means providing a shut off signal for the solenoid valve in response to the movement of the third piston means.
  • a device characterized in that the elastic force means is a spring.
  • a device characterized in that the pressure medium varies in accordance with flight altitude of the engine.
  • control means control both the injection time and injection fuel quantity as a function of the engine parameters.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
  • Fuel-Injection Apparatus (AREA)
US00131713A 1970-04-09 1971-04-06 Device for metering ignition fuel to the ignition unit of an afterburner associated with a turbojet engine Expired - Lifetime US3760590A (en)

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DE2016927 1970-04-09

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FR (1) FR2092306A5 (ja)
GB (1) GB1344341A (ja)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5544480A (en) * 1994-06-30 1996-08-13 The United States Of America As Represented By The Secretary Of The Air Force Augmentor light-off improvement
US5896844A (en) * 1996-10-25 1999-04-27 Hyundai Motor Company Variable fuel injection system for internal combustion engines
US20150308349A1 (en) * 2014-04-23 2015-10-29 General Electric Company Fuel delivery system
US9494209B1 (en) * 2007-06-21 2016-11-15 Bill J. Gartner Regressive hydraulic damper

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105370413B (zh) * 2014-08-25 2017-10-10 中国航发商用航空发动机有限责任公司 航空发动机燃油计量系统及其控制方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479398A (en) * 1945-10-27 1949-08-16 John B Parsons Piston and cylinder assembly embodying a solenoid controlled valve
US3141298A (en) * 1960-11-15 1964-07-21 Rolls Royce Reheat apparatus for a gas turbine engine
US3318091A (en) * 1964-07-15 1967-05-09 Man Turbo G M B H Fuel igniter for a jet turbine engine afterburner
US3611717A (en) * 1969-04-24 1971-10-12 Snecma Device for programming the throughput of fuel supplied to a combustion chamber during an ignition or reignition phase

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479398A (en) * 1945-10-27 1949-08-16 John B Parsons Piston and cylinder assembly embodying a solenoid controlled valve
US3141298A (en) * 1960-11-15 1964-07-21 Rolls Royce Reheat apparatus for a gas turbine engine
US3318091A (en) * 1964-07-15 1967-05-09 Man Turbo G M B H Fuel igniter for a jet turbine engine afterburner
US3611717A (en) * 1969-04-24 1971-10-12 Snecma Device for programming the throughput of fuel supplied to a combustion chamber during an ignition or reignition phase

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5544480A (en) * 1994-06-30 1996-08-13 The United States Of America As Represented By The Secretary Of The Air Force Augmentor light-off improvement
US5896844A (en) * 1996-10-25 1999-04-27 Hyundai Motor Company Variable fuel injection system for internal combustion engines
US9494209B1 (en) * 2007-06-21 2016-11-15 Bill J. Gartner Regressive hydraulic damper
US20150308349A1 (en) * 2014-04-23 2015-10-29 General Electric Company Fuel delivery system
US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube

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FR2092306A5 (ja) 1971-01-21
GB1344341A (en) 1974-01-23

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