US3671172A - Multifuel burner - Google Patents

Multifuel burner Download PDF

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Publication number
US3671172A
US3671172A US24644A US3671172DA US3671172A US 3671172 A US3671172 A US 3671172A US 24644 A US24644 A US 24644A US 3671172D A US3671172D A US 3671172DA US 3671172 A US3671172 A US 3671172A
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US
United States
Prior art keywords
flared section
tunnel
fuel
liquid fuel
wall
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
US24644A
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English (en)
Inventor
Jacques Chedaille
Gerben Koopmans
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.)
Grimes Aerospace Co
Original Assignee
Midland Ross Corp
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
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Application granted granted Critical
Publication of US3671172A publication Critical patent/US3671172A/en
Assigned to FL AEROSPACE CORP. reassignment FL AEROSPACE CORP. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). 9/11/86 AND 1/05/88, OHIO Assignors: MIDLAND - ROSS CORPORATION, CHANGED TO, MIDLAND-ROSS CORPORATION MERGING INTO, MRC MERGER CORP., CHANGED NAME TO
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel

Definitions

  • the flared section of the tunnel is symmetrical in lateral planes and is smoothly contoured into the inner planar surface of the wall.
  • a conical stream of liquid fuel particles is injected into the small end of the flared section so that its conical angle is substantially tangent to the surface of the midsection of the flared section.
  • a gaseous supply tube Surrounding the liquid fuel supply tube is a gaseous supply tube for supplying an annular column of gaseous fuel to the entrance of the flared section.
  • Means are provided for supplying a helically swirling annular column of combustion air adjacent the tunnel surface around the fuel stream or streams.
  • This invention relates to liquid fuel burners of the air swirl type wherein an auxiliary gaseous fuel may be used to enhance the combustion of the liquid fuel. It deals with a burner of this type which produces a flat flame in which combustion is already complete in a plane at right angles to the central burner axis and which is located at a short distance, for example about centimeters, downstream from the plane of the burner outlet for a burner of the size shown in the drawings.
  • the lateral extent of the flame is substantially greater than 30 centimeters.
  • the burner is characterized by the fact that the liquid fuel tube with its discharge nozzle is coaxially arranged within an opening provided in a refractory wall of the enclosure to be heated, the internal end of the opening being outwardly flaring and joining up with the internal face of this wall, without forming a sharp edge, and in that the outlet ports of the nozzle are so directed as to have the fuel jets passing through these ports directed substantially tangential with respect to the flaring section of said opening, preferably in the median zone of said flaring section.
  • the burner is of the multifuel type and includes, in addition to the liquid fuel injector tube, a concentrically disposed gaseous fuel inlet tube which terminates substantially at the beginning of the flaring section of the opening provided in the wall of the enclosure to be heated.
  • FIG. 1 is a sectional view of the burner along 1- 1 of FIG. 2.
  • FIG. 2 is a sectional view of the burner along 2-2 of FIG. 1.
  • the burner 10 includes a refractory wall member 12 of the enclosure to be heated. It may be located in the roof or any other section of the enclosure.
  • the wall section 12 defines a tunnel extending laterally therethrough beginning with a cylindrical tunnel section 14 and terminating with an arcuately flared section 16 which is smoothly contoured into the adjacent planar inner surface of the wall member 12.
  • the curve of the flare may have a radius R equivalent to between about 0.5 to 2.5 times the diameter d of the cylindrical or small end of the flared section 16.
  • radius R is between about 1 to 2 times diameter d.
  • Hyperbolic or other similar curves may also be used provided that the ratio between the diameters of the large and small ends of the flared section is suitably between about 1.521 and 3.511 or preferably between 2:1 and 3:1.
  • the axial length of the flared section 16 is suitably equivalent to about 0.5 to 2.5 times the diameter of the small end of the flared section and preferably about 1 to 2 times the diameter.
  • Liquid fuel is supplied to the flared section 16 by means of a tube member 18 concentrically disposed in the cylindrical section 14 and terminating with a nozzle 20 adjacent the small end of flared section 16.
  • the nozzle 20 is designed so as to at least partially atomize the liquid fuel and produce a hollow cone of liquid fuel particles.
  • the conical angle is such that the conical stream is directed so as to substantially intersect tangentially a midsection of the flared section as shown in FIG. 1 of the drawings.
  • the nozzle may have an annular slot or a series of ports arranged obliquely to the central axis of the burner so that the conical angle, i.e. the angle the fuel jets make with the central axis of the burner, is between about 35 and 55, for example.
  • Gaseous fuel is supplied to the entrance of the flared section 16 by a tube member 21 located concentrically in the cylindrical section 14 of the tunnel.
  • the cylindrical gaseous fuel supply tube 21 has a diameter that is substantially larger than the outside diameter of the liquid fuel tube 18, but smaller than the inside diameter of the cylindrical tunnel section 12.
  • Tube 22 terminates within about 1 diameter of the entrance of the flared section 16 upstream from the liquid fuel nozzle 20.
  • Two annular chambers are formed by this arrangement.
  • the inner chamber 22, that is the chamber formed between the outside of tube 18 and the inside of tube 21, is for supplying an annular column of gaseous fuel arround the liquid fuel.
  • the outer chamber 23 formed between the outside of tube 21 and the inside of tunnel section 12 is for supplying a helically swirling annular column of combustion air to the flared section 16 on the outside of the liquid and gaseous fuel streams.
  • the tube members 18 and 21 are sufliciently long to extend beyond the outside of the enclosure wall whereat they have means for connecting their respective fuel transmission lines.
  • An outer extension 24 is provided for the refractory tunnel. This extension is contained within a larger housing which forms a box 26 for the introduction of combustion air under pressure to the annular combustion air chamber.
  • a swirling means such as a plurality of tangentially directed inlet tubes 28, is provided at the upstream end of the chamber.
  • the inlet tubes communicate between box 26 and the combustion air chamber. They may be arranged in a plane normal to the chamber axis and spaced around the axis at 90 intervals as shown in FIG. 2.
  • combustion air flows under pressure into the box 26 and then into the tube 24 through the inlet passages 28 which induce a swirl in the air flow.
  • the air passes along the annular passage formed by the tubes 24 and 21 and discharges into the heating chamber through the tunnel in the enclosure wall. Due to its swirling movement, this air flows along the wall of the outwardly flaring section 16, forming on this wall a relatively thin stream. Part of this air flow turns back and engenders an annular swirl schematically represented by the arrows 30.
  • the jets of the vaporized steam/fuel or air/fuel mixture flow along the outwardly flaring section 16. Then they encounter the helically swirling annular air stream and mix with this air, combustion taking place downstream of the flaring section 16, along the inside face of the front wall 12.
  • the thus produced flame is very widespread and homogeneous, so that the temperature over the inside face of the Wall 12 is very uniform; the difference between the extreme temperature points amounts to about 15 C. for various furnace temperature levels ranging from 900 to 1400 C.
  • this result is obtained when the said jets are substantially tangential to the median zone 32 of the outwardly flaring section 16.
  • the burner is of the multifuel type in its preferred embodiment. -It is very easy to change over from a liquid fuel to a gaseous fuel, or vice versa, or use both fuels in combination without mechanical alteration or removal of the burner, but simply by opening or closing the fuel valves.
  • the burner when operating on a given liquid or gaseous fuel, can be supplied either with cold air or with hot air.
  • 'Flexibility in operation with cold air is such that at a given air supply pressure, the turndown ranges from 1 to 10 while still ensuring a complete combustion and without making it necessary to supply a higher air flow rate than that corresponding to the stoichiometric combustion of the fuel chose; with air at 300 to 500 C., the turndown range is of 1 to 5, also without air excess.
  • a burner capable of operating on gaseous fuel and liquid fuel separately or in combination with each other to produce a flame which has greater extent in a lateral direction than in an axial direction, said burner comprising: a refractory wall member having a planar inner surface and a tunnel extending laterally therethrough, said tunnel having an arcuately flared exit end section smoothly contoured into said inner surface, said flared section having an axial length equivalent to between 1 to 2 times the diameter of the small end thereof; a liquid fuel injection tube coaxially aligned with said tunnel; a fluid atomizing nozzle located at the discharge end of said tube adjacent the small end of said flared tunnel section to produce a hollow conical stream of atomized fluid directed so that its conical angle is substantially tangent to the surface of a median portion of said flared section; a gaseous fuel injection tube disposed concentrically with and spaced from said liquid fuel injection tube and said tunnel thereby defining two annular chambers, the inner chamber being for supplying gaseous fuel and the outer chamber being for
  • a burner according to claim 1 wherein the curve of the flare has a radius equivalent to about 1 to 2 times the diameter of the small end of the flared section.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
US24644A 1969-03-28 1970-03-30 Multifuel burner Expired - Lifetime US3671172A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6908209A FR2038651A5 (de) 1969-03-28 1969-03-28

Publications (1)

Publication Number Publication Date
US3671172A true US3671172A (en) 1972-06-20

Family

ID=9031017

Family Applications (1)

Application Number Title Priority Date Filing Date
US24644A Expired - Lifetime US3671172A (en) 1969-03-28 1970-03-30 Multifuel burner

Country Status (7)

Country Link
US (1) US3671172A (de)
BE (1) BE748019A (de)
DE (1) DE2013562A1 (de)
ES (1) ES378012A1 (de)
FR (1) FR2038651A5 (de)
GB (1) GB1284807A (de)
LU (1) LU60600A1 (de)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3758263A (en) * 1970-12-16 1973-09-11 Heurtey Sa Fluid-fuel burners
US3836315A (en) * 1971-10-14 1974-09-17 Pyronics Inc Burner apparatus for flame propagation control
US3940234A (en) * 1974-05-28 1976-02-24 John Zink Company Noiseless pms burner
US4050879A (en) * 1974-11-18 1977-09-27 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus
US4055401A (en) * 1975-01-14 1977-10-25 The Ralph M. Parsons Company Reducing gas generator
US4060369A (en) * 1974-10-03 1977-11-29 Schoute Bernardus A Burner for the combustion of hydrocarbonates
DE2801367A1 (de) * 1977-01-14 1978-07-20 Italimpianti Strahler-brenner fuer fluessige brennstoffe
US4154567A (en) * 1977-01-07 1979-05-15 Continental Carbon Company Method and apparatus for the combustion of waste gases
US4249470A (en) * 1978-06-29 1981-02-10 Foster Wheeler Energy Corporation Furnace structure
US4515553A (en) * 1980-04-10 1985-05-07 Kobe Steel, Ltd. Combustion method for reducing the emission of nitrogen oxides
US4976607A (en) * 1986-07-09 1990-12-11 Fuel Tech, Inc. Burner apparatus for providing adjustable flame geometry
DE4307086A1 (de) * 1993-03-06 1994-09-08 Abb Management Ag Brennstoffzuführung für eine Gasturbine
DE4306956A1 (de) * 1993-03-05 1994-09-08 Abb Management Ag Brennstoffzuführung für eine Gasturbine
DE4326802A1 (de) * 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
US5454712A (en) * 1993-09-15 1995-10-03 The Boc Group, Inc. Air-oxy-fuel burner method and apparatus
US5769624A (en) * 1992-09-18 1998-06-23 Luminis Pty. Ltd Variable flame burner configuration
US6461145B1 (en) * 1999-02-25 2002-10-08 Stein Heurtey Flat flame burners
US20090280444A1 (en) * 2008-05-08 2009-11-12 Air Products And Chemicals, Inc. Highly Radiative Burner and Combustion Process
US20100227284A1 (en) * 2006-01-31 2010-09-09 Tenova S.P.A. Flat-flame vault burner with low polluting emissions

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4443182A (en) * 1981-11-10 1984-04-17 Hauck Manufacturing Company Burner and method

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3758263A (en) * 1970-12-16 1973-09-11 Heurtey Sa Fluid-fuel burners
US3836315A (en) * 1971-10-14 1974-09-17 Pyronics Inc Burner apparatus for flame propagation control
US3940234A (en) * 1974-05-28 1976-02-24 John Zink Company Noiseless pms burner
US4060369A (en) * 1974-10-03 1977-11-29 Schoute Bernardus A Burner for the combustion of hydrocarbonates
US4050879A (en) * 1974-11-18 1977-09-27 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus
US4055401A (en) * 1975-01-14 1977-10-25 The Ralph M. Parsons Company Reducing gas generator
US4154567A (en) * 1977-01-07 1979-05-15 Continental Carbon Company Method and apparatus for the combustion of waste gases
DE2801367A1 (de) * 1977-01-14 1978-07-20 Italimpianti Strahler-brenner fuer fluessige brennstoffe
US4203717A (en) * 1977-01-14 1980-05-20 Italimpliant Societa Italiana Impianti Per Asioni Flat flame burner assembly
US4249470A (en) * 1978-06-29 1981-02-10 Foster Wheeler Energy Corporation Furnace structure
US4515553A (en) * 1980-04-10 1985-05-07 Kobe Steel, Ltd. Combustion method for reducing the emission of nitrogen oxides
US4976607A (en) * 1986-07-09 1990-12-11 Fuel Tech, Inc. Burner apparatus for providing adjustable flame geometry
US5769624A (en) * 1992-09-18 1998-06-23 Luminis Pty. Ltd Variable flame burner configuration
DE4306956A1 (de) * 1993-03-05 1994-09-08 Abb Management Ag Brennstoffzuführung für eine Gasturbine
DE4307086A1 (de) * 1993-03-06 1994-09-08 Abb Management Ag Brennstoffzuführung für eine Gasturbine
DE4326802A1 (de) * 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
US5487659A (en) * 1993-08-10 1996-01-30 Abb Management Ag Fuel lance for liquid and/or gaseous fuels and method for operation thereof
US5454712A (en) * 1993-09-15 1995-10-03 The Boc Group, Inc. Air-oxy-fuel burner method and apparatus
US6461145B1 (en) * 1999-02-25 2002-10-08 Stein Heurtey Flat flame burners
US20100227284A1 (en) * 2006-01-31 2010-09-09 Tenova S.P.A. Flat-flame vault burner with low polluting emissions
US8480394B2 (en) * 2006-01-31 2013-07-09 Tenova S.P.A. Flat-flame vault burner with low polluting emissions
US20090280444A1 (en) * 2008-05-08 2009-11-12 Air Products And Chemicals, Inc. Highly Radiative Burner and Combustion Process
US8454354B2 (en) * 2008-05-08 2013-06-04 Air Products And Chemicals, Inc. Highly radiative burner and combustion process

Also Published As

Publication number Publication date
GB1284807A (en) 1972-08-09
ES378012A1 (es) 1972-05-16
BE748019A (fr) 1970-08-31
FR2038651A5 (de) 1971-01-08
LU60600A1 (de) 1970-05-26
DE2013562A1 (de) 1970-10-15

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Legal Events

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AS Assignment

Owner name: FL AEROSPACE CORP.

Free format text: CHANGE OF NAME;ASSIGNORS:MIDLAND-ROSS CORPORATION MERGING INTO;MRC MERGER CORP., CHANGED NAME TO;MIDLAND - ROSS CORPORATION, CHANGED TO;REEL/FRAME:005240/0352

Effective date: 19880926