EP0109585B1 - Brûleur à mazout à vaporisation avec un dispositif de pulvérisation de mazout - Google Patents

Brûleur à mazout à vaporisation avec un dispositif de pulvérisation de mazout Download PDF

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Publication number
EP0109585B1
EP0109585B1 EP83110696A EP83110696A EP0109585B1 EP 0109585 B1 EP0109585 B1 EP 0109585B1 EP 83110696 A EP83110696 A EP 83110696A EP 83110696 A EP83110696 A EP 83110696A EP 0109585 B1 EP0109585 B1 EP 0109585B1
Authority
EP
European Patent Office
Prior art keywords
mixing tube
shield
oil
radial passage
end 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
Application number
EP83110696A
Other languages
German (de)
English (en)
Other versions
EP0109585A1 (fr
Inventor
Erich Adis
Manfred Bader
Winfried Prof. Dr.-Ing. Buschulte
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsche Forschungs und Versuchsanstalt fuer Luft und Raumfahrt eV DFVLR
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
Application filed by Deutsche Forschungs und Versuchsanstalt fuer Luft und Raumfahrt eV DFVLR filed Critical Deutsche Forschungs und Versuchsanstalt fuer Luft und Raumfahrt eV DFVLR
Priority to AT83110696T priority Critical patent/ATE13938T1/de
Publication of EP0109585A1 publication Critical patent/EP0109585A1/fr
Application granted granted Critical
Publication of EP0109585B1 publication Critical patent/EP0109585B1/fr
Expired legal-status Critical Current

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Classifications

    • 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
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle

Definitions

  • the invention relates to a gasification oil burner with an oil atomizing device, a combustion air supply surrounding it, an orifice arranged downstream of the outlet of the oil atomizing device and having an orifice opening, a mixing tube provided coaxially with the orifice opening and a radial passage on the upstream part of the mixing tube, an essentially cylindrical flame tube , the upstream end of which is sealingly connected to the end wall of the combustion air supply which carries the diaphragm, and in which the mixing tube is arranged essentially freely.
  • Such a gasification oil burner is known for example from DE-A-2 918 416 (corresponds to EP-A-0 018 602).
  • the spray generated by the oil atomization device in particular by a pressure swirl nozzle, is injected into the combustion system and at the same time, when flowing through a circular orifice located on the upstream side of the combustion system and arranged concentrically around the nozzle axis, mixed with the combustion air and together with this carried further into the combustion system.
  • This mixture of oil drops and combustion air then enters a mixing tube which is arranged downstream of the orifice and is provided with windows at its upstream end where it adjoins the orifice plate, through which hot recirculation gases are sucked in, owing to the injector effect of the combustion air flow , mixed with the combustion air flow and used to evaporate the fuel drops.
  • the flow rate in the mixing tube of the known arrangement is greater than the flame propagation rate, so that no combustion can stabilize there. For this reason, evaporation of the oil spray droplets is caused in this area only by supplying heat.
  • the cross-sectional widening causes a delay in the flow.
  • the flow velocity passes through the flame propagation velocity at a certain distance from the mixing tube outlet, so that combustion can be established there.
  • the components of the combustion system located upstream of the orifice such as the end wall carrying the orifice, the orifice holder itself and also the combustion air guide tube, are intensively cooled by the combustion air flow, which has approximately ambient temperature.
  • the flame tube and also the mixing tube are in contact with the end wall and / or with the combustion air guide tube in known constructions. There is therefore an intense heat flow from the combustion system and its components into the combustion air duct and its components. In this area, the temperatures of the component walls therefore decrease in the upstream direction.
  • oil burner nozzles for the power range from approx. 65 kW upwards show an increasingly unfavorable spray characteristic for this combustion system.
  • Larger oil film thicknesses and the higher delivery pressures required due to fine atomization and thus higher droplet speeds make the excess fuel in the outer flow area of the mixing tube stronger. As a result, the work situation for the burners worsens with an increasing performance class.
  • the object of the invention is to improve a generic gasification oil burner in such a way that oil and soot formation in the recirculation space and in the area of the orifice plate are reduced, in particular in the case of heating oils with a very high content of aromatic hydrocarbons and / or in the case of excess fuel in the recirculation area.
  • This object is achieved according to the invention in a gasification oil burner of the type described at the outset in that the mixing tube has a closed wall in the section immediately adjacent to the panel, in that the radial passage connects to this mixing tube section with a closed wall and in that the axial length of the between Aperture and radial passage-extending mixing tube section with a closed wall is between 0.1 to 0.6 times the mixing tube diameter.
  • the temperature increase of the components can be controlled by varying the length of the cylindrical mixing tube part between the orifice and the radial passage.
  • a dead space is created in the space between the aperture edge, aperture wall and mixing tube wall up to the radial passage, into which the propellant jet of combustion air and oil mixture which enters through the aperture sucks in hot recirculation gas.
  • the temperature of the recirculation gas is higher and, as a result of the excess fuel, it is ignitable if additional air is added.
  • This fresh air admixture takes place from the combustion air jet entering through the orifice. It can therefore be assumed that the speed reduction in the dead space between the orifice and the mixing tube attachment forms a type of pilot flame which brings about a partial combustion of the excess fuel contained in the recirculation gas.
  • the resulting increase in temperature of the recirculation gases leads to an increase in the temperature level of the propellant jet after admixing to the combustion air space.
  • this promotes the speed of evaporation of the oil drops, on the other hand increases the temperature of the components, in particular the section of the mixing tube downstream of the radial passage, and finally leads to the ignition of the air fuel flow taking place more quickly after leaving the mixing tube.
  • the higher ignitability of the mixture due to the temperature increase achieved in the new design leads to a stabilization of the flame front.
  • the end wall in the area between the mixing tube and the flame tube is offset downstream of the diaphragm, preferably the offset end wall area lies in the same plane as the upstream boundary of the radial passage.
  • this takes the opportunity that deposits can accumulate in the previously existing dead space outside the mixing tube.
  • the staggered wall partly cooled down on its upstream side in the advanced position less by the air flowing into the orifice, so that this also reduces the risk of deposit formation.
  • the inner diameter of the mixing tube section between the orifice and the radial passage differs from that of the mixing tube section located downstream of the radial passage, in particular the inner diameter of the upstream mixing tube section is larger than that of the mixing tube section located downstream of the passage.
  • the end wall can be provided with a thermal insulation layer on its upstream side.
  • a suitable wall temperature can be set by the choice of the insulating material and the insulating material thickness.
  • the gasification oil burner 2 shown in the drawing has a chamber 4, in which a pressure atomizing nozzle 6 is held in the usual way on a nozzle assembly 8.
  • the oil is conveyed by an oil pump 10, which is driven by an electric motor 12, which at the same time drives a fan rotor 14 in a conventional manner.
  • the oil pump 10 conveys the oil into the nozzle block 8 projecting through the atomizer nozzle 6 via an adjustable throttle valve 16 and an electromagnetically operated shut-off valve 18 24, which is adjustable via a motor 26.
  • a pair of ignition electrodes 30 is attached to a holder 28 arranged on the nozzle assembly 8 tert, which is connected to an ignition transformer 32.
  • a diaphragm wall 34 is arranged with a diaphragm passage 36.
  • the aperture 36 is coaxial with the axis of the atomizing nozzle 6.
  • Downstream of the aperture 36 is also arranged coaxially with the axis of the atomizing nozzle 6, a mixing tube 38 which is arranged coaxially in a flame tube 42, the upstream end of which is sealingly connected to an end wall 40.
  • the end wall 40 merges into the diaphragm wall 34 and separates the chamber 4 from the combustion chamber surrounded by the flame tube 42.
  • the diameter of the aperture 36 is smaller than the inner diameter of the mixing tube 38.
  • radial passages 44 are provided, the upstream boundary 46 of which is at a distance from the diaphragm wall 34 which is between 0.1 and 0.6 times the inside diameter of the mixing tube 38.
  • the radial passage 44 is formed by circumferential slots, between which webs 48 remain which connect the upstream mixing tube section 50 and the downstream mixing tube section 52 to one another.
  • the mixing tube section 50 has the same inside diameter as the mixing tube section 52, but within the scope of the invention it is possible to choose the inside diameter of the mixing tube section 50 differently from that of the mixing tube section 52.
  • the extension of the mixing tube section 50 in the axial direction specifically - as mentioned - between 0.1 and 0.6 times the mixing tube diameter.
  • the volume and the geometric dimensions of the dead space 54 can be changed by the variation of the inside diameter and the length of the mixing tube section 50, which is limited on the one hand by the limitation of the aperture passage 36 and the aperture wall 34 surrounding the aperture and on the other hand by the wall of the mixing tube portion 50.
  • the arrangement can be adapted to the operating conditions.
  • an ionization probe 56 protruding through the end wall 40 is provided, which protrudes into the flame tube up to the flame area and which is connected in the usual way to a control device 58, via which the oil supply passes through when the flame is extinguished Closing the valve 18 and switching off the engine 12 is interrupted.
  • FIG. 2 differs from that of FIG. 1 only in the configuration of the end wall 40 and the mixing tube section 50 between the end wall and the radial passage 44. Corresponding parts therefore have the same reference numerals.
  • the inside diameter of the mixing tube section 50 is chosen to be larger than that of the mixing tube section 52.
  • the end wall 40 surrounding the mixing tube section 50 is offset downstream so far that it lies in the same plane as the upstream boundary 46 of the radial passage 44. This avoids the formation of a dead space 60 which surrounds the mixing tube section 50 in the exemplary embodiment in FIG. 1.
  • the end wall 40 carries on its side facing the chamber 4 a thermally insulating layer 62, the choice of material and thickness of which are selected so that the temperature of the end wall 40 guarantees minimal soot deposition on the end wall 40.
  • FIG. 1 it is also possible in the embodiment of FIG. 1 to cover the end wall 40 on its side facing the chamber 4 with an insulating layer 62.

Landscapes

  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Medicines Containing Plant Substances (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Soil Working Implements (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)
  • Catching Or Destruction (AREA)
  • Hydrogen, Water And Hydrids (AREA)

Claims (6)

1. Brûler pour combustible pétrolier par gezéifi- cation (2) comportant un dispositif de pulvérisation du combustible pétrolier, une arrivée, d'air de combustion entourant le dispositif, un diaphragme (34, 36) disposé en aval de la sortie du dispositif de pulvérisation du combustible pétrolier et présentant une ouverture de diaphragme (36), comportant aussi un tube mélangeur (38) prévu coaxialement à l'ouverture de diaphragme et en aval de celle-ci, comportant aussi un passage radial (44) dans la portion amont du tube mélangeur, comportant aussi un tube-foyer (42) essentiellement cylindrique, dont l'extrémité située en amont est reliée, de façon étanche à la paroi d'extrémité (40), qui porte le diaphragme, de l'arrivée d'air de combustion et dans lequel est disposé, essentiellement dégagé, le tube de mélangeur, caractérisé en ce que le tube mélangeur (38) présente, dans sa portion (50) qui jouxte immédiatement le diaphragme (34, 36), une paroi fermée; en ce que le passage radial (44) qui se trouve sur cette portion (50) du tube mélangeur jouxte la paroi fermée; et en ce que la longueur axiale de la portion (50) du tube mélangeur, à paroi fermée, qui s'étend entre le diaphragme (34, 36) et le passage radial (44) a une valeur comprise entre 0,1 et 0,6 fois le diamètre du tube mélangeur.
2. Brûleur pour combustible pétrolier selon la revendication 1, caractérisé en ce que la paroi d'extrémité (40), dans la zone située entre le tube mélangeur (38) et le tube-foyer (42), est décalée vers l'aval par rapport au diaphragme (34, 36).
3. Brûleur pour combustible pétrolier selon la revendication 2, caractérisé en ce que la zone décalée de la paroi d'extrémité (40) est dans le même plan que la limite amont (46) du passage radial (44).
4. Brûleur pour combustible pétrolier selon l'une quelconque des revendications précédentes, caractérisé en ce que le diamètre interne de la portion (50) du tube mélangeur située entre le diaphragme (34, 36) et le passage radial (44) est différent de celui de la portion (52) du tube mélangeur située en aval du passage radial (44).
5. Brûleur pour combustible selon la revendication 4, caractérisé en ce que le diamètre interne de la portion (50) du tube mélangeur située entre le diaphragme (34, 36) et le passage radial (44) est supérieur au diamètre interne de la portion (52) du tube mélangeur située en aval du passage radial (44).
6. Brûleur pour combustible selon l'une quel- quonque des revendications précédentes, caractérisé en ce que la paroi d'extrémité (40) est munie, sur sa face côté chambre (4), d'une couche d'isolation thermique (32).
EP83110696A 1982-11-11 1983-10-26 Brûleur à mazout à vaporisation avec un dispositif de pulvérisation de mazout Expired EP0109585B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83110696T ATE13938T1 (de) 1982-11-11 1983-10-26 Vergasungsoelbrenner mit einer oelzerstaeubungsvorrichtung.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3241730 1982-11-11
DE19823241730 DE3241730A1 (de) 1982-11-11 1982-11-11 Vergasungsoelbrenner mit einer oelzerstaeubungsvorrichtung

Publications (2)

Publication Number Publication Date
EP0109585A1 EP0109585A1 (fr) 1984-05-30
EP0109585B1 true EP0109585B1 (fr) 1985-06-19

Family

ID=6177878

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83110696A Expired EP0109585B1 (fr) 1982-11-11 1983-10-26 Brûleur à mazout à vaporisation avec un dispositif de pulvérisation de mazout

Country Status (10)

Country Link
US (1) US4604104A (fr)
EP (1) EP0109585B1 (fr)
AT (1) ATE13938T1 (fr)
CA (1) CA1227412A (fr)
DE (2) DE3241730A1 (fr)
DK (1) DK158320C (fr)
ES (1) ES8406694A1 (fr)
FI (1) FI72379C (fr)
IE (1) IE55040B1 (fr)
NO (1) NO155115C (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4238529A1 (de) * 1992-11-14 1994-05-19 Deutsche Forsch Luft Raumfahrt Brenner zur Heißgaserzeugung

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT387838B (de) * 1985-12-23 1989-03-28 Bruecker Helmut Dr Oelbrenner
DE3636787A1 (de) * 1986-10-29 1988-05-19 Man Technologie Gmbh Brenner mit einer oelzerstaeubervorrichtung
US5015173A (en) * 1988-06-09 1991-05-14 Vth Ag Verfahrenstechnik Fur Heizung Burner for the combustion of liquids in the gaseous state
DE4009222A1 (de) * 1989-07-13 1991-01-24 Elco Oel & Gasbrenner Brenner zur stoechiometrischen verbrennung von fluessigen oder gasfoermigen brennstoffen
DE3928214A1 (de) * 1989-08-25 1990-03-08 Zimmermann Hans Georg Dipl Ing Brenner mit brenngas-rueckfuehrung fuer fliessfaehige brennstoffe
DE4209221A1 (de) * 1992-03-21 1993-09-23 Deutsche Forsch Luft Raumfahrt Stickoxidarmer brenner
JP4739275B2 (ja) * 2006-08-11 2011-08-03 Ｊｘ日鉱日石エネルギー株式会社 バーナ
US10704469B2 (en) * 2017-07-07 2020-07-07 Woodward, Inc. Auxiliary Torch Ingnition
US10711699B2 (en) * 2017-07-07 2020-07-14 Woodward, Inc. Auxiliary torch ignition
US11421601B2 (en) 2019-03-28 2022-08-23 Woodward, Inc. Second stage combustion for igniter

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2918416A1 (de) * 1979-05-08 1980-11-13 Deutsche Forsch Luft Raumfahrt Vergasungsoelbrenner

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US2424765A (en) * 1942-10-06 1947-07-29 Stewart Warner Corp Hot-air heater having means to recirculate cooled gases
US2857961A (en) * 1954-07-13 1958-10-28 Brown Fintube Co Oil burners
BE656014A (fr) * 1963-11-22
US3685977A (en) * 1969-04-16 1972-08-22 Texas Instruments Inc Partial oxidation of hydrocarbons
DE2059693A1 (de) * 1970-12-04 1972-06-15 Werner Pieper Brenner fuer fluessige Brennstoffe
US3981142A (en) * 1974-04-01 1976-09-21 General Motors Corporation Ceramic combustion liner
DE2511500C2 (de) * 1975-03-15 1983-08-11 Smit Nijmegen B.V., Nijmegen Brenner zur Verbrennung von flüssigem Brennstoff
US4130388A (en) * 1976-09-15 1978-12-19 Flynn Burner Corporation Non-contaminating fuel burner
US4364725A (en) * 1977-01-08 1982-12-21 Deutsche Forschungs- Und Versuchsanstalt Fur Luft- Und Raumfahrt E.V. Blue-flame oil burner
DE2700671C2 (de) * 1977-01-08 1988-07-28 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln Blaubrennender Ölbrenner
US4120639A (en) * 1977-06-30 1978-10-17 Midland-Ross Corporation High momentum burners
DE2821932A1 (de) * 1978-05-19 1979-11-22 Karl Bodemer Mischeinrichtung zur verbrennung von fluessigen kohlenwasserstoffen, insbesondere heizoel und dieseloel
EP0007424B1 (fr) * 1978-06-28 1982-11-24 Smit Ovens Nijmegen B.V. Brûleur pour combustion de carburants liquides
DE3035707A1 (de) * 1980-09-22 1982-04-08 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln Oel- und gasbrenner zum einbau in heizungs- und dampferzeugungskessel

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2918416A1 (de) * 1979-05-08 1980-11-13 Deutsche Forsch Luft Raumfahrt Vergasungsoelbrenner

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4238529A1 (de) * 1992-11-14 1994-05-19 Deutsche Forsch Luft Raumfahrt Brenner zur Heißgaserzeugung
DE4238529C2 (de) * 1992-11-14 1999-02-04 Deutsch Zentr Luft & Raumfahrt Brenner zur Heißgaserzeugung

Also Published As

Publication number Publication date
DE3360303D1 (en) 1985-07-25
DK158320C (da) 1990-10-01
ES527156A0 (es) 1984-08-01
NO155115C (no) 1987-02-11
NO155115B (no) 1986-11-03
DK513783D0 (da) 1983-11-10
NO834103L (no) 1984-05-14
FI834127A (fi) 1984-05-12
DK158320B (da) 1990-04-30
CA1227412A (fr) 1987-09-29
ES8406694A1 (es) 1984-08-01
FI834127A0 (fi) 1983-11-10
DE3241730A1 (de) 1984-05-17
IE832624L (en) 1984-05-11
FI72379C (fi) 1987-05-11
EP0109585A1 (fr) 1984-05-30
FI72379B (fi) 1987-01-30
IE55040B1 (en) 1990-05-09
DK513783A (da) 1984-05-12
ATE13938T1 (de) 1985-07-15
US4604104A (en) 1986-08-05

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