EP0699867A2 - Dispositif de combustion pour combustibles gazeux - Google Patents

Dispositif de combustion pour combustibles gazeux Download PDF

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Publication number
EP0699867A2
EP0699867A2 EP95113665A EP95113665A EP0699867A2 EP 0699867 A2 EP0699867 A2 EP 0699867A2 EP 95113665 A EP95113665 A EP 95113665A EP 95113665 A EP95113665 A EP 95113665A EP 0699867 A2 EP0699867 A2 EP 0699867A2
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EP
European Patent Office
Prior art keywords
burner device
air
tube
fuel
hollow lance
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.)
Withdrawn
Application number
EP95113665A
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German (de)
English (en)
Other versions
EP0699867A3 (fr
Inventor
Johannes Wilhelmus Graat
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Individual
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Individual
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Publication date
Priority claimed from DE19944432395 external-priority patent/DE4432395A1/de
Application filed by Individual filed Critical Individual
Publication of EP0699867A2 publication Critical patent/EP0699867A2/fr
Publication of EP0699867A3 publication Critical patent/EP0699867A3/fr
Withdrawn legal-status Critical Current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 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion

Definitions

  • Such a burner is known from DE 31 13 511 C2.
  • a vortex flow of the fuel-air mixture is generated within the mixing zone and in the downstream combustion zone.
  • the fuel and air supply takes place via at least part of the channels in such a way that the fuel supply line comprises one or more strands running in the wall, which ends or end in one or more of the channels, so that the inflowing fuel from the air flow inside the channels can be detected.
  • a burner device is known from DE-OS 27 29 329, in particular FIG. 12, in which gas can also be supplied to a fuel-air mixing zone bypassing an oil burner.
  • the known burner devices have the disadvantage that they measure relatively high emission values, in particular NOx. This is due to the fact that very intensive mixing is observed, with the result that a short combustion flame is generated in which the temperatures are high and a high proportion of nitrogen oxides is generated relative to the total amount of exhaust gas.
  • DE-OS 43 29 971 A1 describes a burner device which is equipped with a centrally arranged hollow lance which has at least two gas outlet regions which are spaced apart in their axial direction and which ensure the metering of the gas fed into the fuel-air mixing zone .
  • a stabilizing tube which surrounds the hollow lance over part of its length between the swirl generating device and the end of the fuel-air mixing zone.
  • the stabilizing tube has an inside diameter which is at least twice as large as the outside diameter of the hollow lance, and in that the hollow lance has at least one gas outlet region which emerges laterally from the hollow lance and which is inside the stabilizing tube is arranged.
  • the gas is metered and gradually fed into the fuel-air mixing zone.
  • the flame temperature does not reach the high values that result from total mixing.
  • the gas outlet channels are preferably arranged in the jacket and / or in the end face of the hollow lance projecting into the fuel-air mixing zone; However, outlet channels can also be embedded in the end wall of the hollow lance.
  • FIGS. 11) and 1b) show a cross section through a burner device, generally designated 1, which adjoins a boiler wall 2.
  • the burner device 1 has a housing 3 which is essentially cylindrical in shape and encloses several parts.
  • the housing 3 initially surrounds - seen from the outside inwards - a cylindrical air duct 4, to which air is supplied via its opening cross section 5 from a blower (not shown), the pressure in the air duct 4 being above atmospheric pressure. Furthermore, in the front part of the housing 3 there is a center piece 6, which is surrounded by the air duct ends 4 'from the outside.
  • the nozzle part 6 is fitted with its end face 7 in an end wall 8, which is also part of the housing 3.
  • the end wall 8 has the shape of a very flat truncated cone, the smaller base of which is the end face of the nozzle part 6.
  • the end wall 8 also has several, for example twelve, bores 8 ', which are evenly distributed radially symmetrically around the periphery of the end wall surface. Part of the combustion air flows through the bores 8 ′ into the space, which is enclosed by a casing tube 9. This part of the combustion air is about 5 to 35% of the total combustion air.
  • the jacket tube 9 adjoins the end wall 8 and opens to the boiler space 10.
  • the casing tube 9 is provided in the region of the end wall 8 with individual openings 11 which are distributed around the periphery of the casing tube 9. Protruding inwards and then to the openings 11, air baffles 12 are attached to the casing tube 9, which are inclined at an angle of approximately 45 ° and protrude into the casing tube 9 by an amount of 3 to 20% of the inside diameter thereof. Flue gases can be returned from the boiler room 10 and burned through the openings 11. The afterburning of the flue gases results in a lower flame temperature.
  • the neck part 6 is drilled cylindrically along its entire length. This leaves a relatively thick, cylindrical wall 13 which encloses a cavity 13 ', hereinafter referred to as a swirl chamber.
  • a swirl chamber As FIG. 1b shows, the wall 13 is penetrated by numerous slot-like channels 18.
  • the channels 18 deviate in their direction from the normal direction, ie they are tangent to an imaginary circle K within the mixing zone 15.
  • twelve channels for air are provided in the wall 13.
  • the channels 18 are supplied via the air channel 4.
  • a stabilizing tube 22 adjoins the vortex chamber 13 'and has the same inside width as the vortex chamber 13', which for the rest has the same diameter over its entire length.
  • the stabilization tube 22 projects into the fuel-air mixing zone 15 and has the task of stabilizing the vortex. At its end, the diameter of the stabilizing tube 22 decreases somewhat, as can be seen from FIG. 1a.
  • a hollow lance 23 opens into the fuel-air mixing zone 15 concentrically or almost concentrically, the diameter of which is approximately 10 to 40% of the diameter of the fuel-air mixing zone 15 and which in turn is surrounded by the stabilizing tube 22.
  • the hollow lance 23 is designed as a tube with a closed end face 24.
  • the fuel gas flows into the hollow lance 23 from its end facing away from the burner and arrives at jacket bores 26 and 27.
  • the escaping gas is therefore gradually fed into the combustion air flow.
  • the resulting combustion temperatures are lower than in the case of combustion with immediate, total mixing of fuel and air.
  • the hollow lance is surrounded in the interior of the housing 3 and within the stabilizing tube 22 by an air supply line 28 which has inflow openings 28 'and 28' '.
  • the air supply line 28 ends between the foremost and the rearmost gas outlet area. The air flowing through this air supply line absorbs the gas flowing out of the first gas outlet area and feeds it to the air-fuel mixing zone without combustion already taking place in the area of the air supply line.
  • the amount of air that flows through the channels 8 'and 18 and the amount of gas that flows through the casing bores 26, 27 is metered according to the type of gas and the gas pressure present, for example by adjusting the fan pressure.
  • FIGS. 2a) and 2b) a cross section through a further burner device is shown, which is generally designated by 201.
  • the same parts have the same reference numbers as in Figures 1a / 1b.
  • the housing 3 includes a cylindrical air duct 4. Furthermore, in the front part of the housing, there is a center piece 206, which is surrounded by the air duct ends 4 ′ from the outside. The nozzle part 206 is fitted with its end face 7 in the end wall 8. The casing tube 9 connects to the end wall 8, which is part of the housing 3.
  • the nozzle part 206 is drilled cylindrical over its entire length to a swirl chamber 13 '.
  • the stabilizing tube 222 connects to the swirl chamber with the same internal width.
  • An external, adjustable sleeve 216 is provided as the control element, the reciprocating movement of which can either be controlled manually or with the aid of a control device which the sleeve 216 on the basis of sensed values, eg. B. the burning state, or adjusted with the help of a thermostat system or the like.
  • the holes 218 deviate from the normal device, i. H. they are directed tangentially to an imaginary circle K within the fuel-air mixing chamber 215.
  • the bores 218 are therefore at the same time swirl-generating devices which generate a vortex flow by means of the combustion air flowing through them within the swirl chamber 13 'and in the downstream combustion zone 215.
  • the channels 218 can be more or less closed using the sleeve 216.
  • the gas is supplied via a centrally opening hollow lance 223, which is designed as a tube with a closed end face 24.
  • the tube projects beyond the end of the stabilizing tube 222 into the jacket tube 9.
  • the diameter of the hollow lance comprises approximately 25 to 35% of the inner diameter of the stabilizing tube 222.
  • the throughput of fuel gas can be varied through the bores 225 and 225 '.
  • the bores can also be directed tangentially or radially, so that the vortex flow, which is already generated by the inflowing air through the bores 218, is increased.
  • an ionization electrode 29 is inserted, which consists of an insulating jacket 30 and the actual electrode, which ends at the periphery as the outlet opening of the stabilization tube 222.
  • the electrode 29 is used to ignite and to determine whether a flame is present and, if necessary, to emit a signal which indicates the burning state.
  • FIGS. 3a / 3b show a burner device 301 similar to that in FIGS . 2a / 2b.
  • an ignition electrode 31 and an ionization electrode 29 are also installed in the wall 313 of the swirl chamber 313 ′.
  • the hollow lance 323 for the gas supply also protrudes a little further beyond the stabilizing tube 322. Bores 325 and 325 'are embedded in the hollow lance.
  • the casing tube 9 can be pushed back and forth with the air baffles 12, so that the distance between the openings 11 and the end wall 8 is adjustable, which ensures optimal return of the flue gases for controlling the firing temperature.
  • FIG. 4 shows an embodiment in which the bores 418 in the wall 413 of the fuel-air mixing chamber are designed as diffuser or venturi nozzles. This leads to an improvement in swirl development and energy utilization.
  • the subsequent jacket pipe 409 is also provided with a constriction, the narrowest point of which lies just behind the end face 424 of the gas lance 423. The aforementioned fluidic measures improve the energy utilization of the introduced air.
  • FIG. 5 shows a cross section through a burner device, generally designated 501, which adjoins a boiler wall.
  • the burner device 1 has a housing 3 which is essentially cylindrical in shape and encloses several parts.
  • the housing 3 initially surrounds - seen from the outside inwards - a cylindrical air duct 4, to which air is supplied via its opening cross section 5 from a blower (not shown), the pressure in the air duct 4 being above atmospheric pressure. Furthermore, in the front part of the housing 3 there is a center piece 506 which is surrounded by the air duct ends 4 'from the outside. The nozzle part 506 is fitted with its end face into a flat end wall, which is also part of the housing 3.
  • the end wall 8 has several, e.g. twelve, bores 8 ', which are evenly distributed radially symmetrically around the periphery of the end wall surface. Part of the combustion air flows through the bores 8 ′ into the space, which is enclosed by a casing tube 9. This part of the combustion air is about 5 to 35% of the total combustion air.
  • the jacket tube 9 adjoins the end wall 8 and opens to the boiler space 10.
  • the casing tube 9 is provided in the region of the end wall 8 with individual openings 11 which are distributed around the periphery of the casing tube 9. Flue gases can be returned from the boiler room 10 through openings 11 and re-burned. By post-combustion of the flue gases a lower flame temperature.
  • the nozzle part 506 is drilled out cylindrically along its entire length. This leaves a relatively thick, cylindrical wall 513 which encloses a cavity 513 ', hereinafter referred to as a swirl chamber.
  • the wall 13 is penetrated by numerous slot-like channels 18.
  • the channels 18 deviate in their direction from the normal direction, i.e. they are tangent to an imaginary circle within the mixing zone 515.
  • combustion air flows through the channels 18 they are therefore air supply channels and at the same time swirl-generating devices which use the air flowing through them within the swirl chamber 513 'and in the downstream fuel-air mixing zone 515 (framed with dashed lines) generate a vortex movement within the casing tube 9.
  • twelve channels for air are provided in the wall 13.
  • the channels 18 are supplied via the air channel 4.
  • a stabilizing tube 522 adjoins the swirl chamber 513 'and has the same clear width as the swirl chamber 513', which for the rest has the same diameter over its entire length.
  • the stabilization tube 522 protrudes into the fuel-air mixing zone 515 and has the task of stabilizing the vortex.
  • a hollow lance 523 opens out into the fuel-air mixing zone 515 concentrically or almost concentrically, the outer diameter D1 of which is approximately 50% of the inner diameter D2 of the stabilizing tube 522.
  • the hollow lance 523 is designed as a tube with a closed end face 524. The fuel gas flows into the hollow lance 523 from its end facing away from the burner and reaches jacket bores 26.
  • the stabilization tube 522 only protrudes into the edge region of the jacket tube 9.
  • the stabilization tube 522 is relatively short and ends at the edge of the fuel-air mixing zone 515.
  • the amount of air that flows through the channels 18 and the amount of gas that flows through the casing bores 26 is metered according to the type of gas and the gas pressure present, for example by adjusting the fan pressure.
  • An ignition electrode 31 is also embedded in the nozzle part 506.
  • the volume of the swirl chamber 513 ' is limited by an annular insert 32 which partially surrounds the hollow lance from the gas inlet manner and is attached to an annular closure (bottom) 33 of the connecting piece part 506 by means of a screw connection 34.
  • the closure is provided with an axial threaded opening 35 through which the gas is fed into the hollow lance. In the opening 35 is the hollow lance through Screwed in ring 37.
  • the arrangement of the elements 26, 522, 523 and 515 and the use of the insert 34 make it possible to maintain a low flame temperature.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP95113665A 1994-09-03 1995-08-31 Dispositif de combustion pour combustibles gazeux Withdrawn EP0699867A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4432395 1994-09-03
DE19944432395 DE4432395A1 (de) 1993-09-04 1994-09-03 Brennereinrichtung für einen gasartigen Brennstoff

Publications (2)

Publication Number Publication Date
EP0699867A2 true EP0699867A2 (fr) 1996-03-06
EP0699867A3 EP0699867A3 (fr) 1996-09-11

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EP95113665A Withdrawn EP0699867A3 (fr) 1994-09-03 1995-08-31 Dispositif de combustion pour combustibles gazeux

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0867659A1 (fr) * 1997-03-24 1998-09-30 VTH Verfahrentechnik für Heizung AG Procédé et dispositif pour la combustion d'un combustible gazeux
CN110513691A (zh) * 2018-05-21 2019-11-29 安德森热能科技（苏州）有限责任公司 一种双燃料空气涡流燃烧器
CN113819465A (zh) * 2021-08-31 2021-12-21 西安航天动力研究所 一种流量可调节的气氧气甲烷富燃燃气生成装置及方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7736501B2 (en) 2002-09-19 2010-06-15 Suncor Energy Inc. System and process for concentrating hydrocarbons in a bitumen feed
CA2400258C (fr) 2002-09-19 2005-01-11 Suncor Energy Inc. Separateur de mousse bitumineuse a plaques inclinees et methode de traitement d'hydrocarbures a l'aide d'un cyclone separateur
CA2689021C (fr) 2009-12-23 2015-03-03 Thomas Charles Hann Appareil et procede de regulation de debit par le truchement d'une caisse aspirante

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2729321A1 (de) 1977-06-29 1979-01-04 Smit Ovens Nijmegen Bv Verfahren zur regelung der verbrennung von fluessigen brennstoffen
DE3113511C2 (de) 1981-04-03 1986-07-10 Holec Gas Generators B.V., Nijmegen Brennereinrichtung für einen gasartigen Brennstoff
DE4329971A1 (de) 1993-09-04 1995-03-16 Johannes W Graat Brennereinrichtung für einen gasartigen Brennstoff

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1191443A (fr) * 1982-10-13 1985-08-06 Denis Lefebvre Tete de retenue sur bruleurs
FR2582781A1 (fr) * 1985-06-04 1986-12-05 Mueller Rudolf Bruleur pour chaudiere a combustion liquide avec circuit de recyclage des gaz de combustion
ATE111204T1 (de) * 1989-01-09 1994-09-15 Fuellemann Patent Ag Brenner zur verbrennung von gasförmigen brennstoffen und/oder flüssigen brennstoffen in gasförmigem zustand.
AT400259B (de) * 1993-11-29 1995-11-27 Schwarz A & Co Mischeinrichtung für öl- oder gasbrenner

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2729321A1 (de) 1977-06-29 1979-01-04 Smit Ovens Nijmegen Bv Verfahren zur regelung der verbrennung von fluessigen brennstoffen
DE3113511C2 (de) 1981-04-03 1986-07-10 Holec Gas Generators B.V., Nijmegen Brennereinrichtung für einen gasartigen Brennstoff
DE4329971A1 (de) 1993-09-04 1995-03-16 Johannes W Graat Brennereinrichtung für einen gasartigen Brennstoff

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0867659A1 (fr) * 1997-03-24 1998-09-30 VTH Verfahrentechnik für Heizung AG Procédé et dispositif pour la combustion d'un combustible gazeux
CN110513691A (zh) * 2018-05-21 2019-11-29 安德森热能科技（苏州）有限责任公司 一种双燃料空气涡流燃烧器
CN110513691B (zh) * 2018-05-21 2024-04-09 安德森热能科技（苏州）有限责任公司 一种双燃料空气涡流燃烧器
CN113819465A (zh) * 2021-08-31 2021-12-21 西安航天动力研究所 一种流量可调节的气氧气甲烷富燃燃气生成装置及方法
CN113819465B (zh) * 2021-08-31 2024-02-09 西安航天动力研究所 一种流量可调节的气氧气甲烷富燃燃气生成装置及方法

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Publication number Publication date
EP0699867A3 (fr) 1996-09-11

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