US3363661A - Apparatus for producing a flame jet by combusting counter flow reactants - Google Patents

Apparatus for producing a flame jet by combusting counter flow reactants Download PDF

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Publication number
US3363661A
US3363661A US512170A US51217065A US3363661A US 3363661 A US3363661 A US 3363661A US 512170 A US512170 A US 512170A US 51217065 A US51217065 A US 51217065A US 3363661 A US3363661 A US 3363661A
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US
United States
Prior art keywords
air
flame
fuel
burner
flow
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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
US512170A
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English (en)
Inventor
William B Horton
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.)
H E FLETCHER CO
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H E FLETCHER CO
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Filing date
Publication date
Application filed by H E FLETCHER CO filed Critical H E FLETCHER CO
Priority to US512170A priority Critical patent/US3363661A/en
Priority to GB32029/66A priority patent/GB1120326A/en
Priority to DE6606067U priority patent/DE6606067U/de
Priority to DE19661501833 priority patent/DE1501833A1/de
Application granted granted Critical
Publication of US3363661A publication Critical patent/US3363661A/en
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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • 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

Definitions

  • a combustor comprising spaced concentric tubular bodies and having a space for premixing fuel, oxygen and a quantity of nitrogen at one end thereof and a central flame discharge nozzle at the other end thereof.
  • a flame stabilizing wall separates the premixing space from the combustion chamber. Oxygen and nitrogen pass through the space between the tubular bodies and is led in a reversely turned path in the area of the discharge nozzle to provide a secondary flame initiating region.
  • This invention relates to methods and apparatus for Kburning quantities of fuel and oxidant at superatmospheric pressures in a confined space to provide a flame jet and, more particularly, the invention is concerned with a novel technique for bringing together desired quantities of fuel and air in a combustion chamber in a controlled manner so that a greatly extended range of fuel-to-air ratios may be burned stably within the combustion chamber at high through-put velocity.
  • Another object of the invention is to provide a method of controlling the manner in which an oxidant is mixed with fuel so as to accomplish cooling of the flame within an extended range of stable burning.
  • Another object of the invention is to devise improved burner structures for receiving and burning reactants.
  • My improved method of burning is based on the novel concept of providing a primary flow of air which is mixed ICC with fuel and burned initially in a combustion chamber and further providing a secondary flow of air which is injected into an end of the burner chamber opposite to that in which combustion is initiated to thereby set up a counter fiow of air.
  • This counter flow of air is caused to move in opposed relation to the flow of products of combustion to thereby set up a region of extreme turbulence at the exit end of the burner chamber.
  • a highly desirable secondary mixing of fuel with air is produced in very close proximity to the outlet nozzle through which the flame nozzle is emitted.
  • FIGURE 1 is a cross sectional view of a preferred form of burner construction of the invention in which a counter fiow of oxidant may be employed;
  • FIGURE 2 is a fragmentary cross sectional view of a burner generally similar to the burner of FIG. 1 but illustrating a modified form of inlet means for producing a counter flow of oxidant;
  • FIGURE 3 is a cross section taken on the line 3--3 of FIGURE l;
  • FIGURE 4 is a cross section taken on the line 4-4 of FIGURE 1;
  • FIGURE 5 is another cross-sectional view generally corresponding to FIGURE l but further illustrating another modified arrangement for regulating flows of fuel and oxidant independently;
  • FIGURE 6 is a graph showing an air to fuel ratio plotted against temperature changes
  • FIGURE 7 is a cross sectional view of a modified form of burner for secondary flow.
  • FIGURE 8 is a cross section taken on the line 8-8 of FIGURE 7.
  • Patent No. 3,103,251 issued to the assignee of the applicant in the present invention, there has been disclosed a method of flame working a mineral body in which cooling of a flame jet may be realized by employing air as an oxidant, and allowing inert gas in the air to reduce temperature of the flame.
  • the range of fuelto-air ratios used is limited by the need for remaining within a region of stable 'burning to avoid faulty flame operation or flame extinction.
  • I preferably employ a burner construction having a flame stabilizing surface of the class disclosed in application Ser. No. 306,887, and I also make use of the cooling action of quantities of inert gas as referred to in Patent No. 3,103,251.
  • I provide for controlling flow of oxidant in a specific manner to create in a burner charnber a region of high turbulence at a point appreci-ably removed from the llame stabilizing surface and in this way there is created and maintained a secondary flame initiating region.
  • arrow in general refers to a tubular body which is made up of an outer tubular section 12 and an inner tubular portion 13 occurring in spaced relation to the tubular portion 12.
  • Fitted into adjacent ends of the tubular bodies 12 and 13 is a nozzle piece 14 which is .shouldered at 14a to receive an end of the t-ubular member 13 as shown with an extended end of the tubular body 12 being located around a shouldered part 14b of the nozzle piece 14.
  • an injector head 11 against which the tubular section 12 is fitted as shown, and this injector head is formed with an inner annular part 11a having a shouldered .section 11b against which is received the tubular member 13.
  • Numeral 30 denotes a fuel conduit which extends centrally through the member 11 and communicates with an aperture or well 23 in turn leading into the interior of the tubular member 13. Air is supplied under pressure and led through the tubular member 15 into the manifold space 16. Fuel is supplied under pressure through the conduit 36 and passes through the surrounding injector part 31 into the well 23.
  • the nozzle 14 may, if desired, be cooled by a flow of water indicated by arrows, conducted through the annular passage 39 shown at the left hand side of FIGURE 1.
  • the air supplied through the conduit 15 is separated into two independent flows. These flows of air may be referred to conveniently as a primary flow and a secondary flow.
  • the primary flow of air as it enters the annular manifold space 16 passes through a series of openings 22 which communicate with the well 23 and thus allow the air to be discharged through the well into the burner chamber.
  • the secondary flow of air is caused to exit through a plurality of openings 17 from the manifold volume 16 and passes through an annular passageway 18 occurring between tubes 12 and 13 to exert a desirable cooling action with respect to combustor tube 13.
  • This secondary flow of air continues into the end of the burner structure and is there diverted abruptly through a plurality of inlet openings 19 which are arranged around the tubular member 13 and which preferably are formed with an angle as shown in FIGURE 1 so that the air is caused to be substantially reversed in its path of flow and is caused to move in a direction from left to right as viewed in FIGURE 1.
  • the fuel and air leaving the Well 23 by some suitable ⁇ means is ignited and continuously burns to produce a stream of products of combustion, which stream moves at high velocity from right to left as viewed in FIGURE l.
  • the flow of products of combustion containing portions of unburned fuel meets abruptly with the plurality of flows of secondary oxidant or air injected inwardly through the openings 19.
  • an exceedingly highly turbulent region which is generally indicated by arrows at the point noted by numeral 36. Since the .secondary air is being injected around the entire circumference of the burner tube 13, there is created an outer toroidal flow of oxidant which tends to become intimately mixed with the central flow of products of combustion carrying unburned fuel therein.
  • the annular member 11a is formed with a special flame stabilizing surface 11d which tends to promote the formation of a toroidal path of ow of burning material 35 so that this burning material is thrown back upon itself to come into contact with fresh quantities of fuel and oxidant emitted through the well 23 as set forth in application Ser. No. 306,887.
  • FIGURE 6 This latter feature is illustrated diagrammatically in FIGURE 6 in which S denotes the stoichiometric ratio and L1 represents the limits of stable burning of a conventional burner of the class described. In comparison L2 represents the limits of stable burning of the same burner provided with means for employing counter flow oxidant.
  • FIGURE 2 An arrangement of this type has been disclosed in FIGURE 2 for example.
  • the secondary air flow 42 passes through an annular passage 43 contained between tubes 40 and 41.
  • Nozzle piece 44 contains the annular space 45 through which the secondary air flows before becoming discharged through reversely directed annular openings 46. It will be apparent that the secondary air in passing over the relatively large surface area presented by opening 4S and holes ⁇ 46, provides a very substantial cooling effect to the nozzle piece 44.
  • the novel steps of the invention are, in essence, the operations of directing opposed flows of oxidant from two extremities of an enclosed combustion chamber volume.
  • One flow which may be thought of as the primary flow contains fuel.
  • the secondary air flow is provided to assist in burning the fuel which is carried in the stream of products of combustion and to maintain high combustion stability, All of the air so supplied can be consumed in the combustion reaction.
  • this secondary flow of air is heated, having acted as a coolant for the combustor tube 13 as it traveled through the passage 18. This contained heat adds further to t-he flame stabilizing effect of the turbulent region created by this in-put of secondary air.
  • I may desire to modify the structure described in various ways as, for example, in FIGURE 5 I have shown a burner construction similar in all respects to that shown in FIGURE 1 with the exception that the flow of air which is to constitute the primary air may be independently supplied through a valve member V, while the secondary flow of air to constitute the counter flow of the invention may be independently supplied through a valve V1.
  • the flow of air which is to constitute the primary air may be independently supplied through a valve member V
  • the secondary flow of air to constitute the counter flow of the invention may be independently supplied through a valve V1.
  • a burner apparatus for burning liquid fuel, oxygen and a quantity of nitrogen at superatmospheric pressure and producing a nitrogen cooled flame jet said apparatus including an enclosure body having a discharge nozzle formed with a central flame exit aperture, the opposite end of said enclosure body having an annular mixing space for premixing oxygen, nitrogen and liquid fuel droplets, said enclosure body further having a relatively larger combustion chamber communicating with the premixing space, a cylindrical sleeve located around the annular mixing space and the combustion chamber in spaced relation to form an annular passageway which at its intermediate portion is isolated from the interior of the combustion chamber, a flame stabilizing Wall constructed and arranged to separate the premixing space and the combustion chamber, said flame stabilizing wall being formed with a fuel injecting passageway for conducting a fuel mixture from the premixing space into the combustion chamber, said flame stabilizing wall further presenting a at annular flame stabilizing surface which is located around and which extends abruptly away from said fuel injection passageway, said combustion chamber having a predetermined size which defines a volume limited by the quantity

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US512170A 1965-12-07 1965-12-07 Apparatus for producing a flame jet by combusting counter flow reactants Expired - Lifetime US3363661A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US512170A US3363661A (en) 1965-12-07 1965-12-07 Apparatus for producing a flame jet by combusting counter flow reactants
GB32029/66A GB1120326A (en) 1965-12-07 1966-07-15 Method and burner for producing flame jet
DE6606067U DE6606067U (de) 1965-12-07 1966-08-03 Vorrichtung zum erzeugen eines flammstrahls
DE19661501833 DE1501833A1 (de) 1965-12-07 1966-08-03 Verfahren zum Erzeugen eines Flammstrahles und Brenner zur Durchfuehrung dieses Verfahrens

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US512170A US3363661A (en) 1965-12-07 1965-12-07 Apparatus for producing a flame jet by combusting counter flow reactants

Publications (1)

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US3363661A true US3363661A (en) 1968-01-16

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DE (2) DE1501833A1 (de)
GB (1) GB1120326A (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS503159U (de) * 1973-05-04 1975-01-14
EP0007424A1 (de) * 1978-06-28 1980-02-06 Smit Ovens Nijmegen B.V. Brenneranordnung zur Verbrennung flüssiger Brennstoffe
US4257760A (en) * 1978-01-11 1981-03-24 Schuurman Hubert G Cyclone burners
US4384434A (en) * 1980-01-16 1983-05-24 Browning Engineering Corporation High velocity flame jet internal burner for blast cleaning and abrasive cutting
EP0094068A2 (de) * 1982-05-12 1983-11-16 Joh. Vaillant GmbH u. Co. Gebläsebrenner
US4559008A (en) * 1983-01-18 1985-12-17 Deutsche Forschungs- Und Versuchsanstalt Fur Luft-Und Raumfahrt E.V. Starting aid device for a high pressure combustion chamber
EP0421049A1 (de) * 1989-09-08 1991-04-10 Ente Nazionale Per L'energia Elettrica - (Enel) Verbesserungen an einem Brennstoffbrenner für einen Kessel
US6874452B2 (en) 2002-01-15 2005-04-05 Joseph S. Adams Resonant combustion chamber and recycler for linear motors
US20140080072A1 (en) * 2012-09-14 2014-03-20 Eclipse, Inc. Method and apparatus for a dual mode burner yielding low nox emission

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2236394A5 (de) * 1973-07-06 1975-01-31 Gaz De France
FR2379028A1 (fr) * 1977-02-01 1978-08-25 Gaz De France Bruleur metallique a gaz sans premelange et a contre-rotation
DE102005001907B4 (de) * 2005-01-14 2007-05-10 Steinmüller Engineering GmbH Verfahren und Anlage zur Verbrennung eines Brennstoffs

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2515845A (en) * 1946-06-25 1950-07-18 Shell Dev Flame pocket fluid fuel burner
US2725929A (en) * 1951-11-24 1955-12-06 Selas Corp Of America Combustion chamber type burner
US2734560A (en) * 1956-02-14 Burner and combustion system
US3179150A (en) * 1962-04-30 1965-04-20 Gerald D Arnold Furnace
US3224486A (en) * 1964-12-07 1965-12-21 Lorant B Geller Method and apparatus for producing air-fuel flames of sonic and supersonic velocities

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2734560A (en) * 1956-02-14 Burner and combustion system
US2515845A (en) * 1946-06-25 1950-07-18 Shell Dev Flame pocket fluid fuel burner
US2725929A (en) * 1951-11-24 1955-12-06 Selas Corp Of America Combustion chamber type burner
US3179150A (en) * 1962-04-30 1965-04-20 Gerald D Arnold Furnace
US3224486A (en) * 1964-12-07 1965-12-21 Lorant B Geller Method and apparatus for producing air-fuel flames of sonic and supersonic velocities

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5412756Y2 (de) * 1973-05-04 1979-06-02
JPS503159U (de) * 1973-05-04 1975-01-14
US4257760A (en) * 1978-01-11 1981-03-24 Schuurman Hubert G Cyclone burners
EP0007424A1 (de) * 1978-06-28 1980-02-06 Smit Ovens Nijmegen B.V. Brenneranordnung zur Verbrennung flüssiger Brennstoffe
US4384434A (en) * 1980-01-16 1983-05-24 Browning Engineering Corporation High velocity flame jet internal burner for blast cleaning and abrasive cutting
EP0094068A3 (de) * 1982-05-12 1986-03-05 Joh. Vaillant GmbH u. Co. Gebläsebrenner
EP0094068A2 (de) * 1982-05-12 1983-11-16 Joh. Vaillant GmbH u. Co. Gebläsebrenner
US4559008A (en) * 1983-01-18 1985-12-17 Deutsche Forschungs- Und Versuchsanstalt Fur Luft-Und Raumfahrt E.V. Starting aid device for a high pressure combustion chamber
EP0421049A1 (de) * 1989-09-08 1991-04-10 Ente Nazionale Per L'energia Elettrica - (Enel) Verbesserungen an einem Brennstoffbrenner für einen Kessel
US6874452B2 (en) 2002-01-15 2005-04-05 Joseph S. Adams Resonant combustion chamber and recycler for linear motors
US20050145206A1 (en) * 2002-01-15 2005-07-07 Adams Joseph S. Recycler for linear motor
US6997145B2 (en) 2002-01-15 2006-02-14 Adams Joseph S Recycler for linear motor
US20140080072A1 (en) * 2012-09-14 2014-03-20 Eclipse, Inc. Method and apparatus for a dual mode burner yielding low nox emission

Also Published As

Publication number Publication date
DE6606067U (de) 1970-10-01
DE1501833A1 (de) 1969-12-11
GB1120326A (en) 1968-07-17

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