US3810714A - Disposal of liquid spillage and the like - Google Patents

Disposal of liquid spillage and the like Download PDF

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Publication number
US3810714A
US3810714A US00298970A US29897072A US3810714A US 3810714 A US3810714 A US 3810714A US 00298970 A US00298970 A US 00298970A US 29897072 A US29897072 A US 29897072A US 3810714 A US3810714 A US 3810714A
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US
United States
Prior art keywords
fuel
pump
engine
line
drain tank
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
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US00298970A
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English (en)
Inventor
H Turner
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Plessey Overseas Ltd
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Plessey Handel und Investments AG
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Assigned to PLESSEY OVERSEAS LIMITED reassignment PLESSEY OVERSEAS LIMITED ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: PLESSEY HANDEL UND INVESTMENTS AG, GARTENSTRASSE 2, ZUG, SWITZERLAND
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F02C7/232—Fuel valves; Draining valves or systems

Definitions

  • F04b 23/08,F04f 5/48 means of ajet pump fed by fuel from the delivery side [58] Field of Search .,417/79, 80, 81, 87, 89, of the backing pump via a non-return valve, which, 417/1825; 60/3909 F; 239/124, 127 during shut-down of the'engine, prevents flow of fuel from the jet pump into the drain tank under backing- [56] References Cited pump inlet pressure; aspiration of air after emptying of UNITED STATES PATENTS the drain tank is prevented by a float valve.
  • liquid supplied at a suitable pressure by a pump of the system is conducted, in a flow branched off 'the system at the delivery side of the said pump, to form the operation fluid of a jet pump arranged to draw-in the spill liquid and return it, together with the said operating liquid, to the inlet side of the said pump of the system.
  • a gas-turbine engine more particularly a gas-turbine engine of an aircraft
  • the fuel system for an aircraft gas-turbine engine includes a fuel tank 1 equipped with a booster pump 2.
  • This booster pump feeds fuel from the tank 1 to a backing pump 3, which serves to supply the fuel to a high pressure main fuel pump which generally is a metering pump, repesented as a gear pump 4 and arranged to supply a metered quantity of fuel per revolution of the engine to a fuel control unit 5.
  • a fuel? control unit allocates an appropriate flow of fuel to a line 6 feeding the engine burners and returns the excess fuel via a line 7 to the inlet of the metering pump 4.
  • the illustrated arrangement is equipped with a branch line 10 which, when the fuel system is operative again after re-starting of the engine, directs a small portion of the delivery of the backing pump 3 through a unit 11 hereinafter referred-to as drain scavenge unit, -from which the fuel flow from branch line 10, together with aspired fuel from the drain tank 9, is returned to the inlet of the is limited to a single short period at the beginning of each run of the gas turbine.
  • FIG. 1 is a diagram of the fuel system of a gas-turbine engine, more particularly the gas-turbine engine of an aircraft, which incorporates a drain tank and a recovery system according 'to the present invention
  • FIG. 2 is a somewhat diagrammatic sectional elevation of a drain tank and the elements of one form of the recovery system associated therewith, and
  • FlG. 3 is a diagrammatic sectional elevation of a modified recovery system together withra fuel backing pump.
  • the'drain tank 9 is formed with a well '13 which, via a non-rcturnvalvc 1.4 leads to the throat tapping 15 of a jet pump 16, to whose jet nozzle. 17 the branchline 10 is attached "to supply a flow of fuel from the delivery side of the backing pump 3.'This flow together with admixedliquid drawn from the drain tank 9'which has been introduced through the throat tapping 15, then passes through a diffusor portion 19 of the jet pump, where its static pressure increases.
  • the mixture whose pressure has thus been increased, then passes through the feedback line 12, by which it is returned to the inlet side of the backing pump 3.
  • the non-returnvalve 14 has been provided in order to prevent when the engine has been shut down, .and when accordingly backing-pump inlet pressure prevails throughout the jet pump 16, fuel under this pressure from flooding the drain tank 9 by way of the throat tapping -15 of the jet pump 16. Since fuel is only fed to the drain tank 9 fora short period each time when the engine is shut down, it will be appreciated that withdrawal of fuel from the drain 'tank 9 by means of the jet pump 16 should only take place for a short periodafter-re-starting of the engine in order to avoid the risk of aspiration ofair by the jet pump when all the fuel has been withdrawn from the drain tank.
  • the drain tank 9 is preferably equipped with a float 20, which isarranged .to operate a float valve 21 at the bottom of the well 113 so as to prevent, when the level of fuel in the drain tank 9 has fallen to apredetermined limit, the jet pump 16 from withdrawing any further fuel from the tank 9 and well 13, and it will be readily appreciated that if desired,
  • movement of the float may additionally or alternatively by arranged to cut-off the supply of liquid to the jet nozzle 17 through the line 10, thereby limiting the use of energy for the provision of a branch flow through line 12 to the period necessary to empty the drain tank.
  • Such limitation may alternatively be effected by other means, for example by the use of a solenoid valve, and one construction employing this alternative has been illustrated in FIG. 3.
  • the drain tank 9 is connected to the throat inlet 15a of a jet pump 160 without the interposition of a float valve, but a stop valve 22, operable by solenoid 23 against a spring 220 urging the valve to the closed position, is interposed between the branch line 10 from the delivery side of the fuelbacking pump 3 and the jet inlet 17a of the jet pump 16a.
  • the solenoid may be controlled by a pilotoperated switch symbolically indicated at 24 in FIG. 3 or, if desired, by a switch operated by a float similar to the float 20 of FIG. 2.
  • the solenoid When the solenoid is energised, the valve 22 assumes the closed position shown in FIG. 3, in which flow is admitted from line 10 to the jet pump 1611.
  • the switch 24 opens to de-energise the solenoid 23 so that the latter cuts-off the supply of liquid to the jet inlet 17a.
  • the non-return valve has been interposed at 14a between the pump 16a proper and its connection to the feedback line 12 but if desired, the non-return valve may alternatively be arranged in the connection between the tank 9 and the throat inlet 17a of the jet pump, as indicated in broken lines at 14b.
  • the jet pump may, if desired, be fed by fuel from the delivery side of the main fuel pump 4, from which, more particularly when the latter is not of the metering type, the flow feeding the jet pump may be branched off between the main fuel pump and the control unit 5 or, more particularly when the main fuel pump is used for metering purposes, the spill flow in the return line 8 may be utilised to operate the jet pump.
  • the invention may, for example, be employed to return liqnid which has escaped through a shaft seal ofa pump to the inlet side of the pump, even if the pressure at this inlet side is higher than that ofthe escaped liquid, by re-introducing the liquid with the help of a jet pump which is operated by a branch flow from the delivery side of the pump in question and whose diffusor is connected to the inlet side of the same pump.
  • a fuel-supply system for a gas-turbine engine of an aircraft which includes: a source of liquid fuel; an engine-fuel line for supplying fuel to the engine; a fuel pump which has an inlet connected to said source and an outlet leading to said engine-fuel line and which is operable to deliver fuel under pressure to said line; a drain tank at a pressure lower than the pressure at said inlet; control means operable to cut-off delivery to the engine-fuel line from said pump and establish lowresistance communication between said line and the drain tank for facilitating rapid shut-down of the engine; a jet pump having a jet nozzle, an outlet connected to the inlet of said fuel pump, a jet-fuel inlet connected to said engine-fuel line downstream of said fuel pump and leading to said jet nozzle, and an induced-flow inlet; and a drain-fuel return line connecting said drain tank to said induced-flow inlet, said jet pump being operable, after the engine has been restarted subsequently to a shut-down, to withdraw fuel from the drain tank and press
  • a fuel-supply system as claimed in claim 4 which includes a float arranged to rise and fall according to the level of fuel in the drain tank and to operate said cut-off means when that level is below a predetermined minimum.
  • cutoff means include a valve operatively connected to said float so as co cut-off flow through said drained-fuel return line when said level is below a predetermined minimum.
  • cut-off means include means cutting-off the supply of the fuel to the jet nozzle of the jet pump.
  • cutoff means include a solenoid valve.
  • a system as claimed in claim 4 when installed in an aircraft having an engine forming part of the thrustproducing power system thereof, the system being arranged to supply fuel to said engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
US00298970A 1971-10-28 1972-10-19 Disposal of liquid spillage and the like Expired - Lifetime US3810714A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5029271A GB1402996A (en) 1971-10-28 1971-10-28 Fuel-supply systems for gas-turbine engines

Publications (1)

Publication Number Publication Date
US3810714A true US3810714A (en) 1974-05-14

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ID=10455376

Family Applications (1)

Application Number Title Priority Date Filing Date
US00298970A Expired - Lifetime US3810714A (en) 1971-10-28 1972-10-19 Disposal of liquid spillage and the like

Country Status (5)

Country Link
US (1) US3810714A (enExample)
JP (1) JPS4851112A (enExample)
DE (1) DE2251562A1 (enExample)
FR (1) FR2159020A5 (enExample)
GB (1) GB1402996A (enExample)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3894813A (en) * 1974-01-30 1975-07-15 Trw Inc Aircraft fuel supply system having a dual stream tow-phase fluid pump
US4057086A (en) * 1975-02-27 1977-11-08 Healy James W Vapor control
US4877377A (en) * 1987-06-25 1989-10-31 Plessey Overseas Limited Rotary pump system
US5474041A (en) * 1994-12-28 1995-12-12 Cummins Engine Company, Inc. Engine lubrication system with decreased power draw
US5743239A (en) * 1996-06-07 1998-04-28 Fuji Jukogyo Kabushiki Kaisha Fuel pump control system for vehicle
US20050279079A1 (en) * 2003-06-13 2005-12-22 Woodward Governor Company Method to transfer fuel in a fuel system for a gas turbine engine
US20110135505A1 (en) * 2008-06-04 2011-06-09 Continental Automotive Gmbh Pump Device For Feeding Fuel In A Fuel Tank
US20110168133A1 (en) * 2010-05-28 2011-07-14 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US20110168132A1 (en) * 2010-05-28 2011-07-14 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US20120204984A1 (en) * 2009-10-16 2012-08-16 Kautex Textron Gmbh & Co. Kg Fuel tank for a motor vehicle
US8516997B2 (en) 2010-05-28 2013-08-27 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US20160025015A1 (en) * 2014-07-24 2016-01-28 Hamilton Sundstrand Corp Ecology fuel return systems
US20160349766A1 (en) * 2014-07-24 2016-12-01 Hamilton Sundstrand Corporation Ecology fuel return systems
US20180094586A1 (en) * 2016-09-30 2018-04-05 General Electric Company System and method for purging fuel from turbomachine
CN108035916A (zh) * 2017-11-08 2018-05-15 中国航空工业集团公司金城南京机电液压工程研究中心 一种航空燃油射流泵
US10094298B2 (en) * 2015-12-15 2018-10-09 Hamilton Sunstrand Corporation Ecology system ejector pump shutoff valve
CN110067652A (zh) * 2018-01-23 2019-07-30 中国航发商用航空发动机有限责任公司 一种航空发动机供油系统及供油控制方法
US11655735B2 (en) * 2018-06-14 2023-05-23 Safran Aircraft Engines Onboard system and a method for draining an aeroengine

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US5165342A (en) * 1991-08-02 1992-11-24 The Langston Corporation Evacuation system for inking chamber
RU2244143C1 (ru) * 2003-06-04 2005-01-10 ОАО "Омское машиностроительное конструкторское бюро" Устройство дренирования топлива
US8598025B2 (en) 2010-11-15 2013-12-03 Varian Semiconductor Equipment Associates, Inc. Doping of planar or three-dimensional structures at elevated temperatures
FR2994943B1 (fr) * 2012-08-30 2014-09-12 Turbomeca Procede de vidange et collecteur de purge de circuit de carburation d'un helicoptere
FR3010141B1 (fr) * 2013-09-03 2018-01-05 Safran Aircraft Engines Systeme carburant a injecteurs multipoints pour une turbomachine
FR3015567B1 (fr) * 2013-12-19 2015-12-25 Turbomeca Dispositif de drainage de fluides pour un moteur d'aeronef
CN107429709B (zh) 2015-03-09 2019-11-08 戴科知识产权控股有限责任公司 用于使用文丘里效应产生真空的装置
BR112017022110B1 (pt) * 2015-04-13 2023-03-21 Dayco Ip Holdings, Llc Dispositivos para produção de vácuo utilizando o efeito venturi e sistema incluindo um dispositivo para produzir vácuo utilizando o efeito venturi
US10422351B2 (en) 2015-07-17 2019-09-24 Dayco Ip Holdings, Llc Devices for producing vacuum using the venturi effect having a plurality of subpassageways and motive exits in the motive section

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2508260A (en) * 1946-12-31 1950-05-16 George M Holley Fuel feed control for gas turbines
US2664096A (en) * 1947-11-21 1953-12-29 Murdock Mfg & Supply Company Water service fixture
US2953156A (en) * 1957-08-28 1960-09-20 United Aircraft Corp Fuel transfer system
US3043107A (en) * 1960-01-05 1962-07-10 Jr Alexander B Magaus Variable output hydraulic system using fixed displacement pump and variable opening venturi pump
US3547557A (en) * 1968-10-14 1970-12-15 Chandler Evans Inc Fluid pump and delivery system
US3556444A (en) * 1968-02-02 1971-01-19 Entwicklungsring Sued Gmbh Apparatus for the disposal of aircraft engine leakage fluids
US3618909A (en) * 1968-04-30 1971-11-09 Toyota Motor Co Ltd Evaporation-inhibiting device for a carburetor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2508260A (en) * 1946-12-31 1950-05-16 George M Holley Fuel feed control for gas turbines
US2664096A (en) * 1947-11-21 1953-12-29 Murdock Mfg & Supply Company Water service fixture
US2953156A (en) * 1957-08-28 1960-09-20 United Aircraft Corp Fuel transfer system
US3043107A (en) * 1960-01-05 1962-07-10 Jr Alexander B Magaus Variable output hydraulic system using fixed displacement pump and variable opening venturi pump
US3556444A (en) * 1968-02-02 1971-01-19 Entwicklungsring Sued Gmbh Apparatus for the disposal of aircraft engine leakage fluids
US3618909A (en) * 1968-04-30 1971-11-09 Toyota Motor Co Ltd Evaporation-inhibiting device for a carburetor
US3547557A (en) * 1968-10-14 1970-12-15 Chandler Evans Inc Fluid pump and delivery system

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3894813A (en) * 1974-01-30 1975-07-15 Trw Inc Aircraft fuel supply system having a dual stream tow-phase fluid pump
US4057086A (en) * 1975-02-27 1977-11-08 Healy James W Vapor control
US4095626A (en) * 1975-02-27 1978-06-20 Healy James W Vapor recovery in a liquid dispensing unit
US4877377A (en) * 1987-06-25 1989-10-31 Plessey Overseas Limited Rotary pump system
US5474041A (en) * 1994-12-28 1995-12-12 Cummins Engine Company, Inc. Engine lubrication system with decreased power draw
US5743239A (en) * 1996-06-07 1998-04-28 Fuji Jukogyo Kabushiki Kaisha Fuel pump control system for vehicle
US20050279079A1 (en) * 2003-06-13 2005-12-22 Woodward Governor Company Method to transfer fuel in a fuel system for a gas turbine engine
US7007452B1 (en) * 2003-06-13 2006-03-07 Woodward Governor Company Fuel system for a gas turbine engine
US7131274B2 (en) 2003-06-13 2006-11-07 Woodward Governor Company Method to transfer fuel in a fuel system for a gas turbine engine
US20070017206A1 (en) * 2003-06-13 2007-01-25 Woodward Governor Company Ejector pump for a fuel system for a gas turbine engine
US7527481B2 (en) 2003-06-13 2009-05-05 Woodward Governor Company Ejector pump for a fuel system for a gas turbine engine
US20110135505A1 (en) * 2008-06-04 2011-06-09 Continental Automotive Gmbh Pump Device For Feeding Fuel In A Fuel Tank
US9114702B2 (en) * 2009-10-16 2015-08-25 Kautex Textron Gmbh & Co. Kg Fuel tank for a motor vehicle
US20120204984A1 (en) * 2009-10-16 2012-08-16 Kautex Textron Gmbh & Co. Kg Fuel tank for a motor vehicle
US8516997B2 (en) 2010-05-28 2013-08-27 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US9441597B2 (en) 2010-05-28 2016-09-13 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US20110168132A1 (en) * 2010-05-28 2011-07-14 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US8635991B2 (en) 2010-05-28 2014-01-28 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US20110168133A1 (en) * 2010-05-28 2011-07-14 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US8196567B2 (en) 2010-05-28 2012-06-12 Ford Global Technologies, Llc Approach for controlling fuel flow with alternative fuels
US20170191422A1 (en) * 2014-07-24 2017-07-06 Hamilton Sundstrand Corporation Ecology fuel return systems
US20160349766A1 (en) * 2014-07-24 2016-12-01 Hamilton Sundstrand Corporation Ecology fuel return systems
US9624835B2 (en) * 2014-07-24 2017-04-18 Hamilton Sundstrand Corporation Ecology fuel return systems
US20160025015A1 (en) * 2014-07-24 2016-01-28 Hamilton Sundstrand Corp Ecology fuel return systems
US10082084B2 (en) * 2014-07-24 2018-09-25 Hamilton Sundstrand Corporation Ecology fuel return systems
US20190024588A1 (en) * 2014-07-24 2019-01-24 Hamilton Sundstrand Corporation Ecology fuel return systems
US10399690B2 (en) * 2014-07-24 2019-09-03 Hamilton Sundstrand Corporation Ecology fuel return systems
US10094298B2 (en) * 2015-12-15 2018-10-09 Hamilton Sunstrand Corporation Ecology system ejector pump shutoff valve
US20180094586A1 (en) * 2016-09-30 2018-04-05 General Electric Company System and method for purging fuel from turbomachine
US10378447B2 (en) * 2016-09-30 2019-08-13 General Electric Company System and method for purging fuel or coolant from turbomachine
CN108035916A (zh) * 2017-11-08 2018-05-15 中国航空工业集团公司金城南京机电液压工程研究中心 一种航空燃油射流泵
CN110067652A (zh) * 2018-01-23 2019-07-30 中国航发商用航空发动机有限责任公司 一种航空发动机供油系统及供油控制方法
US11655735B2 (en) * 2018-06-14 2023-05-23 Safran Aircraft Engines Onboard system and a method for draining an aeroengine

Also Published As

Publication number Publication date
DE2251562A1 (de) 1973-05-03
JPS4851112A (enExample) 1973-07-18
FR2159020A5 (enExample) 1973-06-15
GB1402996A (en) 1975-08-13

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