US3597141A - Burner device for fluidic fuels - Google Patents

Burner device for fluidic fuels Download PDF

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Publication number
US3597141A
US3597141A US847642A US3597141DA US3597141A US 3597141 A US3597141 A US 3597141A US 847642 A US847642 A US 847642A US 3597141D A US3597141D A US 3597141DA US 3597141 A US3597141 A US 3597141A
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United States
Prior art keywords
burner
tubular
outlet opening
interior
fuel
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Expired - Lifetime
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US847642A
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English (en)
Inventor
Aribert Fracke
Eduard Weber
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Siemens AG
Siemens Corp
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Siemens Corp
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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 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F23C3/006—Combustion apparatus characterised by the shape of the combustion chamber the chamber being arranged for cyclonic combustion

Definitions

  • a burner device for gaseous, liquid or pulverulent fuel comprises a tubular burner structure of a rotationally symmetrical, for example conical or parabolic shape, which tapers from the burner outlet opening toward the much smaller fuel inlet opening.
  • Nozzles for supplying combustion air communicate with the interior of the tapering burner structure in substantially tangential directions respectively and in a plurality of respective planes which extend transversely to the burner axis and are axially spaced from each other.
  • a cylindrical combustion chamber structure is coaxially joined with the tubular burner structure at the outlet opening of the latter and is provided with additional combustion-air supply nozzles which are directed tangentially toward the interior of the combustion chamber.
  • Roughness structures are preferably mounted on the interior wall of the tapering burner structure and may be adjustable as to the height up to which they protrude into the interior of the burner.
  • BURNER DEVICE FOR FLUIDIC FUELS Our invention relates to burner devices for fluidic, i.e. gaseous, liquid or pulverulent fuels, and more particularly to burner devices having an axial fuel supply inlet and an axial gas outlet located opposite the fuel inlet.
  • the burner structure in a burner device generally of the type mentioned above, a circularly symmetrical, namely an approximately conical or substantially parabolic shape which tapers from the relatively wide outlet opening of the tubular structure toward the narrow coaxial fuel inlet end, this tapering burner structure being provided with nozzles for supplying combustion air, which nozzles have respective injecting directions substantially tangential to the burner interior wall surface in mutually spaced planes transverse to the burner axis.
  • the conical or parabolic shape of the tubular burner By virtue of the conical or parabolic shape of the tubular burner, the objectionable formation of a fuel ring in the vicinity of the bottom or fuel inlet region is avoided since the tapering design causes the combustion air to travel along the inner wall surface of the tubular burner from the interior in an outward direction. Furthermore, a stoichiometric combustion and a good controllability of the energy throughput and of the flame character is attained in such a manner that by varying the supply of combustion air, a performance at any desired point over the entire ranges between radiating and nonradiating flame can be obtained.
  • a cylindrical combustion chamber is preferably joined with the outlet end of the conical or tapering burner, and the cylindrical chamber is provided with additional nozzles for the supply of combustion air, these additional nozzles having an injecting direction tangential to the chamber and preferably inclined toward the main flow direction of the tubular burner. This af fords considerably shortening the effective length of the burner.
  • the interior wall of the burner may be provided with roughness structures between the combustion-air nozzles. This secures a combustion with a smaller share ofradiation in the flame.
  • FIG. I shows schematically a lateral view onto a burner device according to the invention having a conically tapering burner portion
  • FIG. 2 shows schematically a cross section through the same burner along the line lI-II in FIG. 1;
  • FIG. 3 is a sectional view of part of a burner having an approximately parabolic shape, and also shows diagrammatically the course of the gas flow in the burner;
  • FIG. 4 shows partly in section a detail of the burner device according to FIGS. 1 and 2.
  • the conical burner 1 (FIGS. 1, 2) or the parabolic burner 1' (FIG. 3) of the illustrated devices is provided with an axial fuel inlet duct 2 adjoining the narrowest end of the tubular tapering shape.
  • Several rows of nozzles 3 to 6 are arranged in tangential relation to the burner-tube jacket in respective planes perpendicular to the axis of the burner device, four such planes being shown for example. Two or more such nozzles may be provided in each of the respective planes, although only two such nozzles are illustrated in each plane.
  • the conically tapering burner l proper is joined with a cylindrical combustion chamber structure 7. This chamber structure has the same diameter as the outlet opening of the tapering burner l and is provided with further nozzles 8 for combustion air.
  • the nozzles 8 extend substantially in tangential directions with respect to the cylindrical combustion chamber 7 and are inclined toward the fuel inlet and consequently toward the main flow direction of the burner device.
  • the total cross-sectional area of the fuel inlet in a device according to the invention is preferably of a lower decimal order of magnitude than'the cross-sectional area of the outlet opening and of the adjacent combustion chamber 7.
  • the ratio of these two areas in the illustrated example is between 25 and 30. That is, the diameter of the fuel inlet end is less than onefifth of the outlet diameter.
  • Bulge-shaped roughness structures 9 are mounted on the interior wall of the burner 1 between the orifices of the respective nozzle rows.
  • the roughness structures are shown to have a straight shape, although they may be curved or be given the shape of a spiral.
  • the nozzle orifices preferably are flush with the inner wall surfaces of the tubular burner l and the combustion chamber 7 so that the roughness structures 9 constitute substantially the only obstacles in the flow path of the gases.
  • FIG. 3 illustrates diagrammatically the course of the com bustion gases inside the tapering burner structure 1 which in this case is approximately parabolical, although the same phenomena occur in a straight cylindrical taper. It is surprising that in such a device, contrary to the known cylindrical cyclone-type combustion chambers, the airflow in the region near the wall does not pass from above downwardly and thence along the innermost, axial region upwardly to the gas outlet. On the contrary, as shown in FIG. 3, the travel course of the combustion gases is just the reverse. As a consequence, the combustion gases travel in the region close to the inner surface from the fuel inlet 2 in an outwarddirection.
  • the air then partially flows toward the axis of the burner and thence inwardly in the direction toward the fuel supply inlet 2.
  • the uppermost nozzle 4, according to FIG. 3 is closed. This has the effect that the core 10 of the flame is displaced downwardly in the direction toward the fuel inlet 2.
  • the nozzles can be supplied with controlled, respectively different quantities of air, and the roughness structures 9 can be displaced to respectively different positions with the combined effect of thereby controlling the recirculation of air so as to attain a good flame stability.
  • a narrower or wider fuel cone can be adjusted as is indicated, for example, by the lines 11 and 12 in FIG. 3. By proper adjustment, the fuel is directed into the flame core 10.
  • the device By providing for variable adjustment of the roughness structures, namely by setting them to protrude more or less deeply into the burner space, the device can be operated with a substantially radiating or nonradiating flame, depending upon the protruding height of the roughness structures.
  • FIG. 4 An embodiment of a roughness structure 9 adjustable in the just-mentioned manner is shown in FIG. 4 with reference to the device according to FIGS. 1 and 2.
  • the roughness structure 9 has a bulging shape and is mounted on a traverse bar 13 whose respective ends are seated on bolts 14 securely fastened to the sheet metal jacket of the conical burner 1.
  • Helical pressure springs 15 and screw nuts 16 permit setting the roughness structure 9 so as to more or less protrude through an opening into the interior of the burner I.
  • a burner device for gaseous, liquid or pulverulent fuel comprising a tubular burner structure having a gas outlet opening and a fuel inlet opening at coaxially opposite ends, said fuel inlet opening having a smaller diameter than said outlet opening and defining a path coaxial to said tubular burner structure for supplying a nonturbulent flow of fuel to said tubular burner structure, said tubular structure having a rotationally symmetrical shape tapering from said outlet opening toward said inlet opening, and a plurality of nozzles supplying combustion air communicating with the interior of said taper ing burner structure in substantially tangential directions respectively and disposed in a plurality of respective planes which extend perpendicularly to the burner axis and are axially spaced from each other, said nozzles being throttleable individually as well as in groups.
  • tubular said tubular burner structure at said outlet opening and having an inner diameter substantially equal to that of said outlet opening.
  • said chamber structure having further substantially tangential nozzles for supply of additional combustion air.
  • said further nozzles being directed at an inclination toward the fuel inflow direction of said fuel inlet.
  • said nozzles having their respective nozzle orifices located substantially at the interior surface of said tapering tubular burner so as to leave the interior of said burner substantially unobstructed.
  • a burner device for gaseous, liquid or pulvcrulent fuel comprising a tubular burner structure having a gas outlet opening and a fuel inlet opening at coaxially opposite ends, said fuel inlet opening having a smaller diameter than said outlet opening, said tubular structure having a rotationally symmetrical shape tapering from said outlet opening toward said inlet opening and nozzle means for supplying combustion air communicating with the interior of said tapering burner structure in substantially tangential directions respectively and in a plurality of respective planes which extend transversely to the burner axis and are axially spaced from each other, said tubular burner structure com rising roughness structures located on its interior surface etween said nozzle orifices and protruding into the interior of said tubular burner structure.
  • a burner device for gaseous, liquid or pulverulent fuel comprising a tubular burner structure having a gas outlet opening and a fuel inlet opening at coaxially opposite ends, said fuel inlet opening having a smaller diameter than said outlet opening, said tubular structure having a rotationally symmetrical shape tapering from said outlet opening toward said inlet opening and nozzle means for supplying combustion air communicating with the interior of said tapering burner structure in substantially tangential directions respectively and in a plurality of respective planes which extend transversely to the I burner axis and are axially spaced from each other, said tubu-

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US847642A 1968-08-07 1969-08-05 Burner device for fluidic fuels Expired - Lifetime US3597141A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19681751839 DE1751839A1 (de) 1968-08-07 1968-08-07 Brenner und Brennkammer fuer gasfoermige,fluessige oder staubfoermige Brennstoffe

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US3597141A true US3597141A (en) 1971-08-03

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US847642A Expired - Lifetime US3597141A (en) 1968-08-07 1969-08-05 Burner device for fluidic fuels

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US (1) US3597141A (enrdf_load_stackoverflow)
AT (1) AT289280B (enrdf_load_stackoverflow)
DE (1) DE1751839A1 (enrdf_load_stackoverflow)
ES (1) ES370281A1 (enrdf_load_stackoverflow)
FR (1) FR2015218A1 (enrdf_load_stackoverflow)
GB (1) GB1265528A (enrdf_load_stackoverflow)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3732070A (en) * 1971-03-31 1973-05-08 Koppers Co Inc Burner
US3848550A (en) * 1971-04-21 1974-11-19 Georgia Tech Res Inst Device for separating solid or liquid particles from a gaseous medium
US4146359A (en) * 1976-06-25 1979-03-27 Occidental Petroleum Corporation Method for reacting nongaseous material with a gaseous reactant
US4257760A (en) * 1978-01-11 1981-03-24 Schuurman Hubert G Cyclone burners
US4294178A (en) * 1979-07-12 1981-10-13 Combustion Engineering, Inc. Tangential firing system
US4586443A (en) * 1977-09-27 1986-05-06 Trw Inc. Method and apparatus for in-flight combustion of carbonaceous fuels
US5359966A (en) * 1992-06-10 1994-11-01 Jensen Donald C Energy converter using imploding plasma vortex heating
US5968378A (en) * 1996-08-21 1999-10-19 Jensen; Donald C. Fuel plasma vortex combustion system
US6237512B1 (en) * 1998-02-03 2001-05-29 Kiyoshi Nakato Waste liquid incinerator and method of incinerating waste liquid
US20100099052A1 (en) * 2002-08-09 2010-04-22 Jfe Steel Corporation Tubular flame burner and combustion control method

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4408256A1 (de) * 1994-03-11 1995-09-14 Abb Management Ag Verfahren und Vorrichtung zur Flammenstabilisation von Vormischbrennern
DE102007015537B4 (de) * 2007-03-30 2009-01-22 Siemens Ag Vergasungsbrenner mit einstellbarem Drall zur Anpassung an wechselnde Betriebsparameter

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1918397A (en) * 1930-03-05 1933-07-18 Jezler Hubert Firing of steam boilers
US2039890A (en) * 1934-07-07 1936-05-05 Coster Henri De Burner
US2800093A (en) * 1951-06-13 1957-07-23 Pollopas Patents Ltd Apparatus for burning pulverized fuel
US3074470A (en) * 1952-04-10 1963-01-22 Owens Corning Fiberglass Corp Liquid fuel burner for forming glass fibers

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1918397A (en) * 1930-03-05 1933-07-18 Jezler Hubert Firing of steam boilers
US2039890A (en) * 1934-07-07 1936-05-05 Coster Henri De Burner
US2800093A (en) * 1951-06-13 1957-07-23 Pollopas Patents Ltd Apparatus for burning pulverized fuel
US3074470A (en) * 1952-04-10 1963-01-22 Owens Corning Fiberglass Corp Liquid fuel burner for forming glass fibers

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3732070A (en) * 1971-03-31 1973-05-08 Koppers Co Inc Burner
US3848550A (en) * 1971-04-21 1974-11-19 Georgia Tech Res Inst Device for separating solid or liquid particles from a gaseous medium
US4146359A (en) * 1976-06-25 1979-03-27 Occidental Petroleum Corporation Method for reacting nongaseous material with a gaseous reactant
US4586443A (en) * 1977-09-27 1986-05-06 Trw Inc. Method and apparatus for in-flight combustion of carbonaceous fuels
US4257760A (en) * 1978-01-11 1981-03-24 Schuurman Hubert G Cyclone burners
US4294178A (en) * 1979-07-12 1981-10-13 Combustion Engineering, Inc. Tangential firing system
US5359966A (en) * 1992-06-10 1994-11-01 Jensen Donald C Energy converter using imploding plasma vortex heating
WO1996010716A1 (en) * 1992-06-10 1996-04-11 Jensen Donald C Energy converter using imploding plasma vortex heating
US5968378A (en) * 1996-08-21 1999-10-19 Jensen; Donald C. Fuel plasma vortex combustion system
US6237512B1 (en) * 1998-02-03 2001-05-29 Kiyoshi Nakato Waste liquid incinerator and method of incinerating waste liquid
US20100099052A1 (en) * 2002-08-09 2010-04-22 Jfe Steel Corporation Tubular flame burner and combustion control method
US20100104991A1 (en) * 2002-08-09 2010-04-29 Jfe Steel Corporation Tubular flame burner
US8944809B2 (en) 2002-08-09 2015-02-03 Jfe Steel Corporation Tubular flame burner and combustion control method

Also Published As

Publication number Publication date
GB1265528A (enrdf_load_stackoverflow) 1972-03-01
DE1751839A1 (de) 1971-08-19
AT289280B (de) 1971-04-13
ES370281A1 (es) 1971-04-01
FR2015218A1 (enrdf_load_stackoverflow) 1970-04-24

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