US3894813A - Aircraft fuel supply system having a dual stream tow-phase fluid pump - Google Patents

Aircraft fuel supply system having a dual stream tow-phase fluid pump Download PDF

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Publication number
US3894813A
US3894813A US437899A US43789974A US3894813A US 3894813 A US3894813 A US 3894813A US 437899 A US437899 A US 437899A US 43789974 A US43789974 A US 43789974A US 3894813 A US3894813 A US 3894813A
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US
United States
Prior art keywords
fuel
stage
pump
flow
centrifugal
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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
Application number
US437899A
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English (en)
Inventor
Paul Cooper
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northrop Grumman Space and Mission Systems Corp
Original Assignee
TRW Inc
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Publication date
Application filed by TRW Inc filed Critical TRW Inc
Priority to US437899A priority Critical patent/US3894813A/en
Priority to GB371475A priority patent/GB1455533A/en
Priority to SE7500897A priority patent/SE404541B/xx
Priority to FR7502807A priority patent/FR2259012B1/fr
Priority to CA218,993A priority patent/CA1012780A/en
Priority to DE19752503823 priority patent/DE2503823A1/de
Priority to JP50012924A priority patent/JPS5217184B2/ja
Application granted granted Critical
Publication of US3894813A publication Critical patent/US3894813A/en
Assigned to PRUDENTIAL INSURANCE COMPANY OF AMERICA, THE, reassignment PRUDENTIAL INSURANCE COMPANY OF AMERICA, THE, SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ARCO-TECH CORPORATION A CORP OF DE
Assigned to AMERITRUST COMPANY NATIONAL ASSOCIATION reassignment AMERITRUST COMPANY NATIONAL ASSOCIATION SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ARGO-TECH CORPORATION, A CORP. OF DE.
Assigned to ARGO-TECH CORPORATION, A CORP. OF DELAWARE reassignment ARGO-TECH CORPORATION, A CORP. OF DELAWARE SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AMERITRUST COMPANY NATIONAL ASSOCIATION
Assigned to ARGO-TECH CORPORATION, A CORP OF DE reassignment ARGO-TECH CORPORATION, A CORP OF DE RELEASED BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: PRUDENTIAL INSURANCE COMPANY OF AMERICA, THE
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04BPOSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B23/00Pumping installations or systems
    • F04B23/04Combinations of two or more pumps
    • F04B23/08Combinations of two or more pumps the pumps being of different types
    • F04B23/12Combinations of two or more pumps the pumps being of different types at least one pump being of the rotary-piston positive-displacement type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/18Rotors
    • F04D29/22Rotors specially for centrifugal pumps
    • F04D29/2261Rotors specially for centrifugal pumps with special measures
    • F04D29/2277Rotors specially for centrifugal pumps with special measures for increasing NPSH or dealing with liquids near boiling-point
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D9/00Priming; Preventing vapour lock
    • F04D9/04Priming; Preventing vapour lock using priming pumps; using booster pumps to prevent vapour-lock
    • F04D9/06Priming; Preventing vapour lock using priming pumps; using booster pumps to prevent vapour-lock of jet type

Definitions

  • An aircraft fuel supply system has a two-stage fuel pump having a first centrifugal booster stage receiving [2%] il-S-il 417/F7$5ib4;;/3Z a main inlet flow Stream and a Second positive i 81 87 89 placement pumping stage and is combined with an 1 o earc 2 2 eductor pump for evacuating liquid and vapor from I high points in the fuel system and for compressing the fluid acted upon to a volume capable of being di- [56] References Clted gested.
  • a flow impeller means constituting a third UNITED STATES PATENTS pump receives the eductor pump discharge completely 2,466,792 4/1949 Conery 417/81 independently of the main inlet flow stream and di- ,5 12/1950 c g y 417/81 rects the fuel acted upon back into the main stream 2345-028 7/1958 Nash a] v r 417/31 ahead of the positive displacement stage, thereby to 1160106 12/1964 Ask/worth 415/109 prevent vapor lock of the positive displacement stage. 3,387,644 6/1968 Hemecke et all...
  • a flow impeller means is provided as a third pump and means form a hydraulic circuit between the eductor pump and the flow impeller means for directing the discharge of the eductor pump to the inlet of the flow impeller means independently of the main inlet flow stream.
  • the flow impeller means are capable of digesting fluid having a volume ratio of vapor-to-liquid of 0.45 or less.
  • the flow impeller means constitutes radial impellers driven by a hub and disk common to the first centrifugal booster stage.
  • a completely separate centrifugal impeller is provided independent of the first centrifugal booster stage and such separate impeller has its own separate pumping chamber.
  • FIG. 1 is a plumbing diagram illustrating the features of an aircraft fuel supply system incorporating the principles of the present invention wherein a completely separate centrifugal pump is used to digest air and vapor acted upon by the eductor.
  • FIG. 2 is a cross-sectional view of an alternative pumping arrangement wherein the flow impeller means constitute radial impellers driven by a hub and a disk common to the first centrifugal boost stage of the aircraft fuel pump.
  • FIG. 1 a conventional source of fuel in an aircraft such as a fuel tank designated by legend and a line leads from the fuel tank to the inlet 11 of a centrifugal first stage 12 of a fuel pump which also includes a second positive displacement stage shown at 13. It will be understood that the pressurized fluid acted upon by the dual stage fuel pump will be directed through a discharge line 14 to a fuel control unit shown diagrammatically at 16, the details of which are not necessary to the understanding of the principles of the present invention.
  • FIG. 1 a high point in the fuel line 10 which is designated at 17 and a line 18 leads to the venturi throat 19 of an eductor pump shown generally at 20.
  • the eductor pump 20 may be powered by fluid obtained from any pressurized source, for example, excess fluid from the flow control unit 16 may be utilized, or a portion of the driving fluid can also be obtained from an interstage point between the centrifugal stage 12 and the positive displacement stage 13 of the fuel pump. In any event, the eductor pump 20 is used to draw air and vapor from the high point 17.
  • the eductor pump Upon sucking off such gas, the eductor pump operates to compress it to a volume capable of being digested as a two phase mixture.
  • a completely separate centrifugal flow impeller means is shown at 21 and a hydraulic circuit means 22 is provided which connects the discharge 23 of the eductor pump 20 to a inlet 24 of the flow impeller means 21.
  • the flow impeller means 21 has means forming its own pumping chamber 26 and a line 27 connects the pumping chamber 26 to the main fuel stream so that the two-phase fluid acted upon by the flow impeller means 21 can be discharged back into the main fuel stream.
  • the line 27 is connected as at 28 to a point after the first centrifugal pumping stage 12, but before the positive displacement pumping stage 13.
  • a pump capable of receiving two fluid streams, each stream being single or twophase, the predominant phase being liquid and the other phase being air and/or vapor of the specific liquid being pumped.
  • the first or mainstream is received at a pressure P and the second or supplementary stream is at a pressure P where P P
  • Both of the impellers of the centrifugal booster stage 12 and the flow impeller means 21 are capable of digesting fluid having a volume ratio of vapor-to-liquid V/L of 0.45 or less, and such impellers discharge pressurized liquid at a pressure P the gaseous phase having been dissolved in the liquid.
  • the flow impeller means constitutes radial impellers driven by a hub and a disk common to the first centrifugal booster stage.
  • the main steam inlet port is shown at 11a and the centrifugal booster impeller is shown generally at 12a and has pumping passages 121 which receive the fluid at a center inlet and discharge the fluid radially outwardly into a toroidal pumping cavity 122.
  • the centrifugal booster stage impeller 12a has a hub formed by a shaft 123 on which is carried an outwardly extending hub flange 124, the hub flange 124 having an axial flange 126 circumjacent the hub shaft 133.
  • On the forward side of the hub flange 124 there are provided a plurality of pumping blades 127, thereby forming pumping passages through which the fluid is directed into the toroidal pumping chamber 122.
  • the pump of FIG. 2 has a mounting pad 128 on which is carried the eductor 20a.
  • the mounting pad 128 is particularly characterized by a supplementary steam inlet port 240 arranged to be in register with a port 130 formed in the eductor 20a and receiving through a passage 131 the gas and fluid acted upon by the eductor.
  • the inlet port 24a is directed to a center lnlet 24b and the flow impeller means, shown generally at 21a, constitutes a plurality of radial impellers 21b which are fastened to the rear side of the hub flange 124 and which operate to deliver the two-phase mixture received from the eductor 20a into the toroidal pumping chamber 122.
  • the hub flange 124 is locked in place on the hub shaft 133 by a bushing 140 which in turn carries a bearing member 141.
  • a drive shaft is keyed as at 142 to the hub shaft 133, which drive shaft is shown at 143.
  • the second stage positive displacement pump constitutes a gear pump and is shown generally at 113.
  • the eductor 20a may be powered at least in part with fluid pressurized by the centrifugal booster impeller 121.
  • an inlet chamber 150 receiving fluid from the pumping chamber 122 via a passage 151. The fluid is directed through a nozzle 152.
  • a port 153 which may be connected to receive gaseous fluid from one or a plurality of high points in the fuel system of the type exemplified by 17 (FIG. 1) and such fluid is sucked through a sleeve 154 into a chamber 156 whereupon it is directed through a venturi passage 157.
  • the nozzle 152 is aligned with the venturi passage 157 and directs a jet of fluid across the space 156 into the venturi passage 157 to accomplish the the eductor action.
  • the two-phase eductor discharge is shown moving in the directions shown by the arrows to the center inlet 24b associated with the flow impeller means 21a.
  • An aircraft fuel supply system comprising, a two-stage fuel pump having a first centrifugal booster stage receiving a main inlet flow stream from a source of fuel and initially pressurizing said main inlet flow stream, said fuel pumping having a second positive displacement pumping stage receiving the initiallized pressurized flow stream and pressurizing said stream for delivery to a fuel flow control unit,
  • an eductor pump for evacuating liquid and vapor from high points in the fuel system and for compressing it to a volume capable of being digested
  • An aircraft fluid fuel pumpingsystem having an integrated air-fluid-vapor lock preventive means comprising:
  • a two-stage pumping means having a first stage comprised of a first centrifugal boost pump discharging to a second stage comprised of a positive displacement gear pump and being operable in such a manner that the output of said first stage is greater than the input capacity of said second stage, I t
  • an eductor pumping means connected to said high point accumulation chambers and receiving a motive flow including said excess output from said first stage thereby operable to draw said air-fuelvapor accumulations into said eductor pumping means to produce a two-phase flow
  • a second centrifugal flow impeller means and hydraulic circuit means extending between an output portion of said eductor pumping means and an inlet portion of said second centrifugal flow impeller means, whereby said two-phase flow is pressurized to a level equal to that of the output pressure of said first centrifugal boost pump, and hydraulic circuit means for introducing the regenerated air-fuelvapor accumulations into the main fuel flow of the system ahead of said positive displacement pump and after said first centrifugal boost pump.
  • said se cond centrifugal flow impeller means being mounted on a common disk and head of said first centrifugal boost pump, and having a separate inlet receiving a two-phase fluid flow comprised of said air-fuel-vapor and the motive fluid flow discharged boost pump, and radially discharged into said toroifrom said eductor pumping means, wherein said dal output chamber of said first stage centrifugal tw-phasc fluid flow is pressurized to a level equal boost pump. to the output pressure of said first stage centrifugal

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
US437899A 1974-01-30 1974-01-30 Aircraft fuel supply system having a dual stream tow-phase fluid pump Expired - Lifetime US3894813A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US437899A US3894813A (en) 1974-01-30 1974-01-30 Aircraft fuel supply system having a dual stream tow-phase fluid pump
GB371475A GB1455533A (en) 1974-01-30 1975-01-28 Aircraft fuel supply systems
SE7500897A SE404541B (sv) 1974-01-30 1975-01-28 Brensletillforselsystem for flygplan
CA218,993A CA1012780A (en) 1974-01-30 1975-01-29 Aircraft fuel supply system having a dual stream two-phase fluid pump
FR7502807A FR2259012B1 (ko) 1974-01-30 1975-01-29
JP50012924A JPS5217184B2 (ko) 1974-01-30 1975-01-30
DE19752503823 DE2503823A1 (de) 1974-01-30 1975-01-30 Brennstoffspeisesystem fuer ein flugzeug

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US437899A US3894813A (en) 1974-01-30 1974-01-30 Aircraft fuel supply system having a dual stream tow-phase fluid pump

Publications (1)

Publication Number Publication Date
US3894813A true US3894813A (en) 1975-07-15

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ID=23738390

Family Applications (1)

Application Number Title Priority Date Filing Date
US437899A Expired - Lifetime US3894813A (en) 1974-01-30 1974-01-30 Aircraft fuel supply system having a dual stream tow-phase fluid pump

Country Status (7)

Country Link
US (1) US3894813A (ko)
JP (1) JPS5217184B2 (ko)
CA (1) CA1012780A (ko)
DE (1) DE2503823A1 (ko)
FR (1) FR2259012B1 (ko)
GB (1) GB1455533A (ko)
SE (1) SE404541B (ko)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4627792A (en) * 1984-03-15 1986-12-09 Grundfos A/S Rotating flow pump with a feed pump unit formed as an ejector
US9482225B2 (en) * 2012-06-04 2016-11-01 Honeywell International Inc. Gear pump, pumping apparatus including the same, and aircraft fuel system including gear pump
CN112443436A (zh) * 2019-09-03 2021-03-05 普拉特 - 惠特尼加拿大公司 具有喷射泵的共轨燃料系统以及其使用方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6121535U (ja) * 1984-07-13 1986-02-07 株式会社 サカエプロセス 哺乳びん
GB8925402D0 (en) * 1989-11-10 1989-12-28 British Hydromechanics Pumping liquid/gas mixture
FR2699986B1 (fr) * 1992-12-29 1995-02-24 Inst Francais Du Petrole Dispositif et méthode permettant de transférer dans une seule conduite un effluent de type polyphasique.

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2466792A (en) * 1947-01-24 1949-04-12 F E Myers & Bro Company Jet pumping system and apparatus
US2533028A (en) * 1948-11-24 1950-12-05 Ingersoll Rand Co Pumping system
US2845028A (en) * 1954-10-25 1958-07-29 Jacuzzi Bros Inc Shallow well expanded output pump
US3160106A (en) * 1962-03-08 1964-12-08 Abrasive Dev Centrifugal pumps
US3387644A (en) * 1966-09-15 1968-06-11 Mc Donnell Douglas Corp Fuel vapor and air eductor system
US3532441A (en) * 1968-09-04 1970-10-06 Chandler Evans Inc Pumps with vapor handling element
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
US3810714A (en) * 1971-10-28 1974-05-14 Plessey Handel Investment Ag Disposal of liquid spillage and the like

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2466792A (en) * 1947-01-24 1949-04-12 F E Myers & Bro Company Jet pumping system and apparatus
US2533028A (en) * 1948-11-24 1950-12-05 Ingersoll Rand Co Pumping system
US2845028A (en) * 1954-10-25 1958-07-29 Jacuzzi Bros Inc Shallow well expanded output pump
US3160106A (en) * 1962-03-08 1964-12-08 Abrasive Dev Centrifugal pumps
US3387644A (en) * 1966-09-15 1968-06-11 Mc Donnell Douglas Corp Fuel vapor and air eductor system
US3532441A (en) * 1968-09-04 1970-10-06 Chandler Evans Inc Pumps with vapor handling element
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
US3810714A (en) * 1971-10-28 1974-05-14 Plessey Handel Investment Ag Disposal of liquid spillage and the like

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4627792A (en) * 1984-03-15 1986-12-09 Grundfos A/S Rotating flow pump with a feed pump unit formed as an ejector
US9482225B2 (en) * 2012-06-04 2016-11-01 Honeywell International Inc. Gear pump, pumping apparatus including the same, and aircraft fuel system including gear pump
CN112443436A (zh) * 2019-09-03 2021-03-05 普拉特 - 惠特尼加拿大公司 具有喷射泵的共轨燃料系统以及其使用方法

Also Published As

Publication number Publication date
SE7500897L (ko) 1975-07-31
JPS50124010A (ko) 1975-09-29
SE404541B (sv) 1978-10-09
GB1455533A (en) 1976-11-10
JPS5217184B2 (ko) 1977-05-13
FR2259012A1 (ko) 1975-08-22
DE2503823A1 (de) 1975-08-21
CA1012780A (en) 1977-06-28
FR2259012B1 (ko) 1980-04-11

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AS Assignment

Owner name: PRUDENTIAL INSURANCE COMPANY OF AMERICA, THE,

Free format text: SECURITY INTEREST;ASSIGNOR:ARCO-TECH CORPORATION A CORP OF DE;REEL/FRAME:005437/0698

Effective date: 19900630

Owner name: AMERITRUST COMPANY NATIONAL ASSOCIATION

Free format text: SECURITY INTEREST;ASSIGNOR:ARGO-TECH CORPORATION, A CORP. OF DE.;REEL/FRAME:005443/0153

Effective date: 19900630

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Owner name: ARGO-TECH CORPORATION, A CORP OF DE

Free format text: RELEASED BY SECURED PARTY;ASSIGNOR:PRUDENTIAL INSURANCE COMPANY OF AMERICA, THE;REEL/FRAME:005559/0287

Effective date: 19901224

Owner name: ARGO-TECH CORPORATION, A CORP. OF DELAWARE

Free format text: SECURITY INTEREST;ASSIGNOR:AMERITRUST COMPANY NATIONAL ASSOCIATION;REEL/FRAME:005576/0273

Effective date: 19901224