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WO1992007179A1 - Systeme d'amenee de carburant - Google Patents

Systeme d'amenee de carburant Download PDF

Info

Publication number
WO1992007179A1
WO1992007179A1 PCT/US1991/006363 US9106363W WO9207179A1 WO 1992007179 A1 WO1992007179 A1 WO 1992007179A1 US 9106363 W US9106363 W US 9106363W WO 9207179 A1 WO9207179 A1 WO 9207179A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
pump
exhaust port
supply system
ejector
Prior art date
Application number
PCT/US1991/006363
Other languages
English (en)
Inventor
John R. Williamson
Original Assignee
Allied-Signal Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Allied-Signal Inc. filed Critical Allied-Signal Inc.
Publication of WO1992007179A1 publication Critical patent/WO1992007179A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C14/00—Control of, monitoring of, or safety arrangements for, machines, pumps or pumping installations
    • F04C14/02—Control of, monitoring of, or safety arrangements for, machines, pumps or pumping installations specially adapted for several machines or pumps connected in series or in parallel
    • 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
    • F02C7/236—Fuel delivery systems comprising two or more pumps

Definitions

  • This invention relates to fuel supply systems for gas turbine engines and more specifically to an improved fuel supply system and method that includes a dual displacement pump and an ejector boost pump.
  • a typical fuel supply system includes a fuel tank, several stages of fuel 0 pumps, and a fuel control which meters the fuel and feeds the fuel to the engine's combustor.
  • a fuel control which meters the fuel and feeds the fuel to the engine's combustor.
  • Within these several pump stages there is usually one engine driven, positive displacement pump which is the main pump in the system and at least one low pressure pump that maintains lb a minimum pressure at the inlet to the main pump to prevent cavitation therein.
  • Positive displacement pumps discharge fuel flow at a rate that is proportional to the rotational speed of the pump. Because this pump is driven by the engine the rotational speed of the pump is
  • the term light-off refers to the point during the start sequence of a gas turbine engine at which the conditions in the combustor are suitable to support combustion. Generally, light-off occurs at an engine rotational speed which is about 10-12% of the engines full operating speed. Therefore, the pump is sized at a rotational speed of about 10-12% of the pumps operating speed. However, while the fuel discharged by the pump is linearly proportional to the speed of the pump such a relationship does not hold for the engines. Therefore, when the engine reaches its operating speed, referred to as 100% speed, the pump also reaches its 100% speed and discharges more fuel flow than is needed by the engine.
  • U.S. Patent No. 4,339,917 discloses a fuel supply system which includes a first stage ejector pump, a second stage compressor and a third stage, engine driven positive displacement pump. Excess fuel exiting from the third stage pump is sent to a hydraulic turbine which drive the second stage compressor. A portion of the flow exiting the second stage compressor is used to drive the first stage ejector pump. Because all the stages are ultimately driven by the engine a reservoir of fuel just upstream of the third stage is required to supply fuel during an engine start sequence.
  • U.S. Patent No. 4,703,136 discloses a fuel supply system which includes a first stage ejector pump, a fuel filter, and a second stage engine driven positive displacement pump. Excess fuel exiting from the positive displacement pump is injected through the ejector pump thereby using the temperature of this fuel to prevent ice from forming in the filter.
  • Turner et al. U.S. Patent No. 3,736,072 discloses a fuel supply system including a first stage electric boost pump, a second stage backing pump, a third stage ejector pump and a fourth stage engine driven positive displacement pump. After the engine has been started excess fuel is directed from the fuel control back to the ejector pump. Once the ejector pump is operating, the first stage pump is shut down.
  • U.S. Patent No. 3,043,104 discloses a fuel supply system including a first stage ejector pump, a second stage ejector pump and a third stage engine driven, fixed displacement pump. Excess fuel is sent form the fuel control back to the ejector pumps.
  • the engine driven pump In each of the above mentioned system the engine driven pump must operate at full capacity when the engine is operating at 100% speed regardless of the altitude and thereby generates a large temperature rise in the fuel.
  • a need exists for a fuel supply system that can provide sufficient fuel flow to light off a gas turbine engine at sea level and can provide fuel flows less than the system's full capacity when the gas turbine engine is at its operating rotational speed.
  • An object of the present invention is to provide a fuel supply system that can provide sufficient fuel flow to light off a gas turbine engine at sea level and can provide fuel flows less than the system's full capacity when the gas turbine engine is at its operating rotational speed.
  • a dual displacement pump also referred to as a dual pressure pump, is a pump capable of generating two fuel flows at the same or different pressures depending on the conditions downstream of the pump's exit ports. At altitude the flow from one of the exit ports is at full pressure and is sent to the engine while the flow from the second port, which is at a lower pressure, can be recirculated. Because it is not possible to operate this lower pressure discharge port at 0 psig backpressure, this excess discharge pressure is put to use by feeding the fuel flow therefrom into an ejector pump upstream of the dual displacement pump.
  • the single FIGURE is a partially schematic, partially cross-sectional diagram of a fuel supply system contemplated by the present invention.
  • a fuel supply system generally denoted by the numeral 10 is shown in conjunction with a gas turbine engine 12 having an associated gear box 14 which drives a positive displacement pump 40 through a mechanical connection shown schematically by dotted line 18.
  • the pump 40 feeds pressurized fuel through delivery conduit 20 to a fuel control shown schematically at 22 for subsequent delivery to the engine 12.
  • the fuel supply system 10 further includes a fuel tank 24 having a low pressure pump 26 having driving means independent of the engine 12 and disposed within the tank 24 so that the pump 26 is gravity fed even when the tank 24 is almost empty.
  • the pump 26 is an electric boost pump.
  • Fuel is pumped by the pump 26 through a conduit 28 to an eductor type intake port 32 of an ejector or jet boost pump 30 that effects an aspirating action in drawing fuel through conduit 28 when the pump 26 is not operating.
  • the ejector 30 further includes aspirating nozzle means in the form of a nozzle 34 disposed in alignment with an eductor type exhaust port 36. Fuel flow exiting from the exhaust port 36 is directed to the pump 40.
  • the pump 40 is preferably a dual displacement or dual pressure gear pump comprising a housing 50 with three pumping gears 44, 46 and 48 mounted therein.
  • the gears 44, 46 and 48 are arranged so that the gear 46 intermeshes with both gears 44 and 48.
  • Each of the gears 44, 46, 48 are carried on rot ta le shafts, 54, 56 and 58 respectively.
  • the shaft 56 is rotatably driven by the gear box 14. As the shaft 56 drives gear 46 counterclockwise, the gear 46 drives the gears 44 and 48 clockwise. Accordingly, the gear 44 and 46 form a first gear pump and the gears 46 and 48 form a second gear pump in parallel flow arrangement with the first gear pump.
  • the pump 40 can be either a fixed displacement or variable displacement pump. However, the fixed displacement configuration is preferred because it is simpler, more reliable and less costly.
  • the housing 50 has a first inlet 51 and a first outlet 52 disposed generally on a common tangent between the gears 44 and 46, and a second inlet 53 and a second outlet 54 disposed generally on a common tangent between the gears 46 and 48.
  • the inlets 51 and 53 are on opposite sides of the housing 50 as are the outlets 52 and 54. Both inlets 51 and 53 receive fuel flow from the exhaust port 36.
  • the fuel exiting outlet 52 is pumped through the delivery conduit 20 while the fuel exiting outlet 54 is pumped to a valve means 60.
  • the housing 50 would also enclose the ejector pump 30.
  • the valve means 60 shown schematically, is embodied, for example, as an actuatable, two-position valve.
  • the valve 60 is positioned by an actuator 61 controlled from the fuel control system 22 shown schematically by dotted line 63. In a first position, the valve means 60 directs the fuel pumped through outlet 54 to the delivery conduit 20, and in a second position this fuel is directed to the nozzle 34 in the ejector 30.
  • the electric boost pump pumps fuel from the tank 24 to the pump 30, and the valve means 60 is positioned to direct the fuel flow therethrough to the delivery duct 20.
  • the combustor of the gas turbine engine lights-off and the engine begins to accelerate.
  • the pump 26 is shut off and the valve means 60 is repositioned to direct the flow through the valve means 60 to the ejector 30.
  • the fuel flow entering the ejector 30 is accelerated by the nozzle 34 so that the stream of fuel exiting the nozzle 34 has a much larger velocity than the stream of fuel flowing through the intake port 32. As these two fuel streams mix, the velocity of the slower stream is increased creating a sectioning effect which draws fuel from the fuel tank 24.
  • a pressure relief valve 65 is provided to direct any fuel not used by the ejector back to the fuel tank 24.
  • the advantages of the present invention are that it can provide sufficient fuel flow at low engine speeds and also, effectively reduced fuel flows at higher engine speeds. Also, it is more efficient than the prior art systems, because at the higher engine speeds the fuel flow at outlet 54 is at a lower pressure than the fuel flow at outlet 52. Additional efficiency is gained by using the energy of this lower pressure flow to drive the ejector 30.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Système d'amenée de carburant (10) destiné à l'alimentation en carburant d'un moteur à turbine à gaz (12), comprenant une pompe électrique de suralimentation de premier étage (26), une pompe à éjecteur de deuxième étage (30) qui ne fonctionne que lorsque la pompe électrique de suralimentation (26) ne fonctionne pas et une pompe à double déplacement, entraînée par moteur, de troisième étage (40).
PCT/US1991/006363 1990-10-15 1991-09-05 Systeme d'amenee de carburant WO1992007179A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US59791490A 1990-10-15 1990-10-15
US597,914 1990-10-15

Publications (1)

Publication Number Publication Date
WO1992007179A1 true WO1992007179A1 (fr) 1992-04-30

Family

ID=24393440

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1991/006363 WO1992007179A1 (fr) 1990-10-15 1991-09-05 Systeme d'amenee de carburant

Country Status (1)

Country Link
WO (1) WO1992007179A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19647799C1 (de) * 1996-11-19 1998-04-16 Pumpenfabrik Ernst Scherzinger Brennstoffverteiler
DE10127196A1 (de) * 2001-06-05 2002-12-12 Rolls Royce Deutschland Verfahren zur Brennstoffversorgung sowie Brennstoffversorgungssystem für ein mit zumindest einer Fluggasturbine versehenes Flugzeug
US6857441B2 (en) 2001-05-11 2005-02-22 Roper Pump Company Fluid metering device
EP1559884A3 (fr) * 2004-01-29 2008-12-17 United Technologies Corporation Système pour l'alimentation en carburant d'un moteur à turbine pour aéronef comprenant un désaérateur
WO2014112484A1 (fr) * 2013-01-18 2014-07-24 株式会社Ihi Système de carburant
EP3670866A1 (fr) * 2018-12-19 2020-06-24 Hamilton Sundstrand Corporation Systèmes de carburant d'aéronef et procédés de pressurisation de carburant

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2812715A (en) * 1954-06-23 1957-11-12 Westinghouse Electric Corp Fuel system
GB1180095A (en) * 1966-04-04 1970-02-04 Snecma Adjustable Mixer for Plants Conveying Fluid Within a Large Range of Flow Rates.
US3551073A (en) * 1968-12-16 1970-12-29 Chandler Evans Inc Pumping system with improved jet inducer
US3736072A (en) * 1970-08-25 1973-05-29 Plessey Handel Investment Ag Systems for the supply of liquid fuel to gas-turbine engines
DE2830598A1 (de) * 1977-08-19 1979-03-01 Garrett Corp Stroemungsmittelpumpeinrichtung

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2812715A (en) * 1954-06-23 1957-11-12 Westinghouse Electric Corp Fuel system
GB1180095A (en) * 1966-04-04 1970-02-04 Snecma Adjustable Mixer for Plants Conveying Fluid Within a Large Range of Flow Rates.
US3551073A (en) * 1968-12-16 1970-12-29 Chandler Evans Inc Pumping system with improved jet inducer
US3736072A (en) * 1970-08-25 1973-05-29 Plessey Handel Investment Ag Systems for the supply of liquid fuel to gas-turbine engines
DE2830598A1 (de) * 1977-08-19 1979-03-01 Garrett Corp Stroemungsmittelpumpeinrichtung

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19647799C1 (de) * 1996-11-19 1998-04-16 Pumpenfabrik Ernst Scherzinger Brennstoffverteiler
US6857441B2 (en) 2001-05-11 2005-02-22 Roper Pump Company Fluid metering device
EP1388131A4 (fr) * 2001-05-11 2005-12-21 Roper Pump Company Dispositif de mesure de liquides ameliore
DE10127196A1 (de) * 2001-06-05 2002-12-12 Rolls Royce Deutschland Verfahren zur Brennstoffversorgung sowie Brennstoffversorgungssystem für ein mit zumindest einer Fluggasturbine versehenes Flugzeug
EP1264975A3 (fr) * 2001-06-05 2004-02-04 Rolls-Royce Deutschland Ltd & Co KG Système d' alimentation en carburant pour un réacteur
US6810671B2 (en) 2001-06-05 2004-11-02 Rolls-Royce Deutschland Ltd & Co Kg Method for the fuel supply and a fuel supply system for aircraft equipped with at least one aero gas turbine
EP1559884A3 (fr) * 2004-01-29 2008-12-17 United Technologies Corporation Système pour l'alimentation en carburant d'un moteur à turbine pour aéronef comprenant un désaérateur
WO2014112484A1 (fr) * 2013-01-18 2014-07-24 株式会社Ihi Système de carburant
JP2014137053A (ja) * 2013-01-18 2014-07-28 Ihi Corp 燃料システム
US9828916B2 (en) 2013-01-18 2017-11-28 Ihi Corporation Fuel system
EP3670866A1 (fr) * 2018-12-19 2020-06-24 Hamilton Sundstrand Corporation Systèmes de carburant d'aéronef et procédés de pressurisation de carburant
US11267580B2 (en) 2018-12-19 2022-03-08 Hamilton Sundstrand Corporation Fuel systems for aircraft and methods of pressurizing fuel

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