US3796203A - Fuel atomization - Google Patents

Fuel atomization Download PDF

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Publication number
US3796203A
US3796203A US00217497A US3796203DA US3796203A US 3796203 A US3796203 A US 3796203A US 00217497 A US00217497 A US 00217497A US 3796203D A US3796203D A US 3796203DA US 3796203 A US3796203 A US 3796203A
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United States
Prior art keywords
jet
collector
nozzle
fuel
orifice
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
Application number
US00217497A
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English (en)
Inventor
N Moss
M Broad
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Eaton Corp
Original Assignee
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
Assigned to EATON CORPORATION reassignment EATON CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: PLESSEY OVERSEAS LIMITED
Assigned to EATON CORPORATION reassignment EATON CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: PLESSEY COMPANY PLC, THE
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/34—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by ultrasonic means
    • F23D11/345—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by ultrasonic means with vibrating atomiser surfaces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M21/00—Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/005—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M2700/00—Supplying, feeding or preparing air, fuel, fuel air mixtures or auxiliary fluids for a combustion engine; Use of exhaust gas; Compressors for piston engines
    • F02M2700/12—Devices or methods for making a gas mixture for a combustion engine
    • F02M2700/123—Fuel supply devices

Definitions

  • the impact surface may be struck by the jet when it is deflected, for example by an electromagnet acting through an armature on a flexible tube whose end forms the orifice, or when the collector orifice is moved out of line of the jet, or a separate baffle may be arranged to penetrate into the path of the jet without moving the orifice or the jet relative to each other.
  • apparatus for supplying to a mixture-burning combustion device a controlled supply of liquid fuel comprises a jetforming nozzle, means for continuously feeding to said nozzle a liquid fuel under pressure to normally form a solid jet of liquid fuel passing across a chamber or passage containing a combustion-sustaining gas into a collector aperture so arranged as to intercept such solid jet and conduct the fuel in it out of said chamber or passage, and meansoperable to so interfere with the normal flow from said nozzle as to break-up and prevent at least some of the liquid forming the solid jet from entering the collector aperture.
  • the measns operable to interfere with the normal flow of the jet may be operated periodically for a time variable in accordance with the fuel requirements of the combustion device.
  • deflecting-means may be provided which are operable to cause all, or a preferably adjustable part, of the fuel in the jet to impact on a surface and fragment into a spray of droplets, thereby preventing during such operation removal by the collector aperture of the fuel, or of such part of the fuel, issuing from the nozzle.
  • the deflecting means may be arranged to deflect the nozzle and thereby the jet out of alignment with the collector aperture.
  • the deflecting means may be arranged to deflect the collector aperture out of alignment with the nozzle.
  • the surface on which the jet impacts may be an end surface of a collector tube forming the aperture, or it may be a surface extending from such collector aperture, while a further possibility is the use of a baffle to act as an impact surface separate from the element containing the collector aperture, in which case the deflecting means may be arranged to control penetration of this baffle into the cross-section of the jet without affecting the mutual alignment of the nozzle and the collector aperture.
  • the impact surface may be at an angle other than normal to the direction of flow of the jet from the nozzle, thereby causing a spray of droplets to be directed in a particular direction and if required to form a spray of a particular shape, e.g., a fan-shaped spray.
  • the means of deflecting either the nozzle, element containing the collector aperture, or the baffle may be an electromagnet attracting or repelling the element in question, or two electromagnets, arranged on opposite sides of the element to be moved, in order to move the element in both directions, control being effected by varying the degree of deflection and/or the ratio of the time in which the fuel is, due to such deflection, atomised by reaching the impact surface to the time in which there is no deflection and in which therefore substantially all the fuel in the jet is removed through the collector tube.
  • the deflection may be effected by subjecting the nozzle at spaced time intervals to vibratory movements which may be of a high or ultrasonic frequency to cause the jet, during the time of such operation, to be periodically deflected and impact on the said surface.
  • the nozzle and the collector aperture may be inserted in the air inlet duct to the engine and the jet arranged to strike an impact surface during each induction cycle for a period dependent on the momentary fuel requirements of the engine.
  • the movement of the nozzle, baffle, or collector aperture may be in the form of a discrete pulse, in which case the length of the pulse in conjunction with the flow rate of fuel in the jet and the amplitude of the movement will determine the quantity of fuel reaching the engine at each pulse.
  • pulses of oscillation of a frequency high compared to the pulse frequency may be applied to the tube or nozzle or baffle in a direction transverse to that of the jet.
  • the quantity of fuel reaching the engine or other consumer is determined by the duration of each pulse of oscillations and the pulse frequency.
  • the frequency of the oscillations is not critical and may be in the infrasonic, sonic or ultrasonic range.
  • FIG. 1 is an elevational diagram showing an arrangement including a fixed nozzle and a movable collector tube
  • FIGS. 2 and 3 similarly show respectively two arrangements each including a movable nozzle and a fixed collector tube
  • FIG. 4 similarly shows an arrangement in which a nozzle is oscillated
  • FIG. 5 shows a modified arrangement having a fixed nozzle and a fixed collector tube, in conjunction with a movable baffle, and
  • FIG. 6 shows a detail of an arrangement similar to that of FIG. l but having a modified impact surface.
  • a fuel-supply tank 1 is connected by a line 2 to a fuel pump 3, which pressu-- rises the fuel and supplies it through a delivery line 4 to the nozzle 5 which is so shaped as to normally provide a coherent jet 7 of fuel.
  • a collector tube 6 constitutes the shorter one of two straight parallel tubular portions joined by a semicircular tubular portion to form a collector structure 8, and its bore is arranged to be normally aligned with the jet of fuel issuing from the nozzle 5, so that normally all, or substantially all, the fuel issuing from the nozzle will enter the inlet aperture or collector orifice 9 of the collector tube 6 and pass through the tube structure 8 and a fuel-return line 10 to be returned to't he inlet of the pump 3, to be recycled through the system.
  • the structure 8 is mounted resiliently, or made resilient itself to permit movement of its inlet aperture 9 transversely to the jet 4, and an electromagnet 11 is arranged to co-operate with a magnetic armature 12 secured to the longer leg of the tube structure 8 to move, when the electromagnet is energised, the collector aperture 9 at the free end of the collector tube 6 transversely out of alignment with the jet 7 so that at least a portion of the cross-section of the jet 7 will impinge on an impact surface 90 provided on the end portion of the collector tube and will be broken-up by the impact into a spray of droplets.
  • the nozzle and the inlet 9 end of the collector tube 6 are arranged in-such manner in the induction line 50 of a combustion engine 51, which may be a reciprocating-piston engine, that when the electromagnet 1 I is de-energised, the solid jet 7 extends across the flow of air in the induction line 50 to reach the inlet aperture 9 of the collector tube 6, and
  • substantially no fuel will be conveyed to the engine by the induced air flow in the line 50.
  • the electromagnet I1 is energised to attract its armature 12
  • the resulting movement of the armature will displace the collector structure from the position shown in full lines at 8 to the position shown in broken lines at 8', thereby displacing the inlet aperture of the collector tube 6 fromthe full-line position 9 in alignment with the jet 7 to the brokenline position 9', which is laterally to the right, in the Figure, of the jet 7.
  • the jet will therefore no longer reach the collector tube.
  • the impact surface will move from the fullline position 9a laterally of the jet 7 into the position shown in broken lines at 9a; which is in the line of the jet 7.
  • the jet 7 will therefore impinge on the surface 9a, the jet will be broken-up by the impact, and the resulting small particles of the liquid fuel will be reflected by the impact surface to form a spray cone, indicated at 57, which extends across the air flow in the induction line 50, and due to the large surface-to-volume ratio of the small particles, the fuel will be suspended in the air in droplet form and will thus be conveyed to the engine.
  • a nozzle which, similarly to nozzle 5 of FIG. 1, forms the fuel supplied by a pump 3 into a coherent jet 22 normally aligned with a fixed collector tube 21, is flexibly mounted at 23 so that it may be pivotally moved to a position in which the jet 22 passes laterally of the inlet aperture of the collector tube 21.
  • an electromagnet 24 is arranged to act upon an armature 25 secured to the nozzle 20.
  • the coherentjet 22 of fuel is deflected out of alignment with the collector aperture of the tube 21 so as to impinge on an impact surface 21g which is attached to the inlet end of the collector tube 21 laterally of its orifice, and the impact will break-up the jet of fuel similarly to the action of the impact surface 9a in the embodiment described with reference to FIG. 1.
  • An adjustable stop 52 limiting the approach of the armature 25 to the magnet 24 is provided to permit adjustment of the part of the crosssection of the jet in which, when the magnet is energised, the fuel of the jet will impact on the surface 21 to be fragmented into a spray of droplets which are carried away by the flow of combustion air in the passage 50 and thus prevented from being removed by the colleetor orifice.
  • a nozzle 30 forms the fuel supplied by the pump 3 into a coherent jet 34, which is normally aligned with a collector tube 35.
  • This nozzle extends at right angles from a resiliently flexible tube 32, so that flexure of the tube 32 will result in angular deflection of the jet 31 without substantial transverse movement of the nozzle 30 itself.
  • An electromagnet 33 acting in the direction of the jet 31 of fuel on a magnetic armature 34 secured to the tube 32 is provided to deflect the tube and thus alter the direction of the jet 34 while the centre of the nozzle 30 remains substantially on the lineof the axis of the collector tube 35.
  • a nozzle 40 forms the fuel supplied by the pump 3 into a coherent jet 42 normally aligned with a collector tube 41, and a piezoelectric vibrator 43 is arranged when energised to vibratorily move the nozzle 40 perpendicularly to its axis, thus causing the jet 42 to move in periodic fashion into and out of alignment with the inlet aperture of a fixed collector tube 41.
  • the frequency of the vibrator is high in relation to the length of each period or pulse of energisation of the vibrator, this will cause, during each period of energisation, a predetermined portion of the fuel supplied by the jet to miss the collector inlet orifice and be broken-up by impact to be carried with the combustion air along the induction line, while the remaining portion of the fuel forming the jet 42 will reach the collector inlet orifice and will thus be returned to the inlet side of the pump 3.
  • the vibrator frequency may be as high as to be in the ultrasonic range.
  • both the nozzle 5 and the collector inlet aperture 9 are fixed in mutually aligned positions, the aperture 9 being formed in a wall 15.
  • a baffle element 13 separate from the member 15 containing the collector orifice 9, is prpvided and arranged to be movable into and out of engagement with the coherent jet 7.
  • the baffle 13 is connected to the armature 12 of the electromagnet I1 and a spring assembly 14 is arranged to urge the baffle 13 to a position clear of the jet, while the electromagnet is so arranged that when it is energised, its armature will move the baffle 13 against the spring action into the line of the jet 7.
  • the movement-of the nozzle, tube or the impact surface may alternatively be effected by two electromagnets respectively operative to move the elements into and out of alignment with each other.
  • the spray of fuel after impingement of thejet can be varied in its shape and its direction, and a suitable built-up lug or the like may be formed on the collector tube close to its inlet end to provide the impact surface for the jet. Such an arrangement is illustrated in FIG.
  • the nozzle and collector tube may, as illustrated in FIG. 1 be mounted in the air induction passage leading to the combustion chamber or chambers of the engine so that the fuel may be mixed with the combustion air before it enters the combustion chamber, and the frequency and the length of the periods in which during each induction stroke or each revolution of the engine, the jet is wholly or partly prevented from reaching the collector aperture, may be automatically controlled in response to the fuel requirements of the engine, for example by a control system somewhat similar to that described in the complete specification of British Pat. No. 1,138,536.
  • Apparatus for supplying controlled amounts of liquid fuel to a mixture-burning combustion device which comprises a passage member having a passage for conveying combustion air to the combustion device, a jetforming fuel-nozzle member having a nozzle arranged to discharge a solid jet of fuel into said passage, means for continuously feeding to said nozzle liquid fuel under pressure, a fuel-collector member having a collector orifice in said passage and forming a line leading from said orifice to a point outside said passage, said collector orifice being normally so aligned with said nozzle as to intercept the whole of said solid jet of fuel, an impact member having an impact surface approximately facing said nozzle but normally displaced laterally from the line of said solid jet so as to be clear of said jet, and control means operable for moving at least one of said members to so alter the relative alignment of said members as to cause at least part of the cross-section of said solid jet to strike said impact surface thereby causing the fuel conveyed in said part of the cross-section to be scattered by the impact and deflected in atomized
  • Apparatus as claimed in claim 1 which includes automatic means which cause the said control means to be operated periodically for a time variable in accordance with the fuel requirements of the combustion device.
  • control means include an electromagnet for producing the movement of at least one of said members.
  • Apparatus as claimed in claim 2 which further includes a reciprocatory combustion engine having an operating cycle that includes an induction stroke, said passage being connected to said engine for supplying fuel-and-air mixture to the engine, and said automatic means being arranged to operate said control means during each induction stroke of the engine for a period of a length dependent on the momentary fuel requirements of the engine.
  • control means are adjustable to vary the portion of the cross-section of the jet that strikes the impact surface.
  • Apparatus as claimed in claim 1 wherein the disposition of the impact surface to a surface normal to the jet is such as to render the reflected spray asymmetrical relative to the axis of the jet, or non-circular in cross-section.
  • control means include transducer means operable to produce when energised vibratory movement of one of said members transversely to the direction of said solid jet.
  • control means include transducer means operable to produce when energised vibratory movement of said nozzle member transversely to. the direction of said

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Fuel-Injection Apparatus (AREA)
US00217497A 1971-01-18 1972-01-13 Fuel atomization Expired - Lifetime US3796203A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB224571 1971-01-18

Publications (1)

Publication Number Publication Date
US3796203A true US3796203A (en) 1974-03-12

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Application Number Title Priority Date Filing Date
US00217497A Expired - Lifetime US3796203A (en) 1971-01-18 1972-01-13 Fuel atomization

Country Status (7)

Country Link
US (1) US3796203A (OSRAM)
CA (1) CA960104A (OSRAM)
FR (1) FR2122904A5 (OSRAM)
GB (1) GB1323995A (OSRAM)
IT (1) IT946650B (OSRAM)
NL (1) NL7200614A (OSRAM)
SE (1) SE373187B (OSRAM)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB717525A (en) * 1951-02-14 1954-10-27 Moto Guzzi Societa Per Azioni System of carburation in internal combustion engines, and a carburetter embodying the system
US3319613A (en) * 1965-06-03 1967-05-16 Electronic Specialty Co Fuel injection system
US3465732A (en) * 1967-10-19 1969-09-09 Physics Int Co Piezoelectric control valve
US3598096A (en) * 1970-01-28 1971-08-10 Gen Motors Corp Fuel metering system
US3613649A (en) * 1969-06-25 1971-10-19 Plessey Co Ltd Fuel injection systems for internal-combustion engines fed with a fuel-and-air mixture
US3616782A (en) * 1968-12-27 1971-11-02 Nippon Denso Co Fuel supply device for internal combustion engines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB717525A (en) * 1951-02-14 1954-10-27 Moto Guzzi Societa Per Azioni System of carburation in internal combustion engines, and a carburetter embodying the system
US3319613A (en) * 1965-06-03 1967-05-16 Electronic Specialty Co Fuel injection system
US3465732A (en) * 1967-10-19 1969-09-09 Physics Int Co Piezoelectric control valve
US3616782A (en) * 1968-12-27 1971-11-02 Nippon Denso Co Fuel supply device for internal combustion engines
US3613649A (en) * 1969-06-25 1971-10-19 Plessey Co Ltd Fuel injection systems for internal-combustion engines fed with a fuel-and-air mixture
US3598096A (en) * 1970-01-28 1971-08-10 Gen Motors Corp Fuel metering system

Also Published As

Publication number Publication date
FR2122904A5 (OSRAM) 1972-09-01
IT946650B (it) 1973-05-21
SE373187B (OSRAM) 1975-01-27
CA960104A (en) 1974-12-31
GB1323995A (en) 1973-07-18
NL7200614A (OSRAM) 1972-07-20

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AS Assignment

Owner name: EATON CORPORATION, 100 ERIEVIEW PLAZA, CLEVELAND,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:PLESSEY COMPANY PLC, THE;REEL/FRAME:004148/0818

Effective date: 19830524

Owner name: EATON CORPORATION, 100 ERIEVIEW PLAZA, CLEVELAND,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:PLESSEY OVERSEAS LIMITED;REEL/FRAME:004142/0890

Effective date: 19830524