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EP0775869A2 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

Info

Publication number
EP0775869A2
EP0775869A2 EP96810756A EP96810756A EP0775869A2 EP 0775869 A2 EP0775869 A2 EP 0775869A2 EP 96810756 A EP96810756 A EP 96810756A EP 96810756 A EP96810756 A EP 96810756A EP 0775869 A2 EP0775869 A2 EP 0775869A2
Authority
EP
European Patent Office
Prior art keywords
channel
premix burner
fuel
burner according
vortex generators
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.)
Granted
Application number
EP96810756A
Other languages
German (de)
English (en)
Other versions
EP0775869A3 (fr
EP0775869B1 (fr
Inventor
Klaus Dr. Döbbeling
Adnan Dr. Eroglu
Peter Dr. Senior
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.)
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP0775869A2 publication Critical patent/EP0775869A2/fr
Publication of EP0775869A3 publication Critical patent/EP0775869A3/fr
Application granted granted Critical
Publication of EP0775869B1 publication Critical patent/EP0775869B1/fr
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
    • 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
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
    • F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to a premix burner for the combustion of gaseous and / or liquid fuel, in which the fuel is injected as a secondary flow into a gaseous, channeled main flow, the secondary flow having a substantially smaller mass flow than the main flow.
  • a premix burner is known from EP 0 321 809 B1, which is characterized by low NOx emission values (approx. 25 ppm) and high flame stability.
  • This premix burner also known as a double-cone burner, consists of hollow, part-cone bodies, which complement one another, with tangential air inlet slots for the combustion air flowing in from the compressor, and feeds for gaseous and liquid fuels, the center axes of the hollow part-cone bodies having a cone inclination widening in the direction of flow and in Longitudinally offset to each other.
  • a fuel nozzle for the liquid fuel is arranged inside the burner (cone tip), through which the fuel is injected into the hollow cone at an acute angle.
  • the resulting tapered liquid fuel profile is enclosed by the tangentially rotating combustion air flow, the concentration of the fuel continuously decreasing in the axial direction due to the mixing with the combustion air.
  • the premix burner can also be operated with gaseous fuel or in mixed operation.
  • the mixture of the gaseous fuel with the combustion air already takes place in the tangential air inlet slots, into which the gaseous fuel is introduced via uniformly distributed nozzles.
  • a further permanent reduction in the pollutant emission values of the double-cone burners, for example to NOx values less than 9 ppm, by changing the operating conditions is not possible because of the problems with flame stability, pulsation and the ever increasing combustion temperatures.
  • EP 0 619 456 A1 discloses a fuel supply system for a combustion chamber with premix combustion, in which a gaseous and / or liquid fuel is injected as a secondary flow into a gaseous, channeled main flow, the secondary flow being a much smaller one Mass flow has as the main flow and the flow through the premixing channel has curved walls.
  • the channel is ring-shaped and an equal number of vortex generators are strung together in the circumferential direction on the outer and inner ring wall.
  • These vortex generators have three freely flowing surfaces that extend in the direction of flow, one of which forms the roof and the other two the side surfaces.
  • the side surfaces are flush with the same duct wall and enclose an arrow angle ⁇ with one another.
  • the roof surface lies with an edge selling transversely to the flow channel against the same channel wall as the side surfaces and the longitudinal edges of the roof surface, which are flush with the longitudinal edges of the side surfaces projecting into the flow channel, run at an angle of attack ⁇ to the channel wall.
  • Half vortex generators are also possible, in which only one of the two side surfaces of the vortex generator is provided with an arrow angle ⁇ / 2, while the other side surface is aligned straight and in the direction of flow.
  • the connecting edges of two opposing vortex generators can lie on the same radial or be offset by half a division.
  • the invention has for its object to develop a premix burner for the combustion of gaseous and / or liquid fuel, with which extremely low NOx emissions are achieved, the burner should be characterized by a simple geometry and a reliable operating behavior.
  • the burner an intimate mixture of combustion air and fuel is to be achieved within a very short distance, with a simultaneous uniform distribution of speed in the mixing zone, and furthermore, with such a burner, a blowback of the flame is to be avoided with certainty without the use of a mechanical flame holder.
  • a premix burner according to the preamble of claim 1, which works with a fuel supply system which is known from EP 0 619 456 A1, in that the vortex generators used produce vortices which, after the fuel has been mixed with the air the fuel / air mixture flow leave a residual vortex that the annular main flow channel formed by the channel walls has a constant height downstream of the vortex generators and the fuel injection, which is in the range between 5 to 20 times its height and that the annular main flow channel then widens to a circular main flow channel by closing the inner cylinder wall.
  • the advantages of the invention are that the fuel supply system and the use of the vortex generators on the one hand result in an intensive, complete mixing of fuel and combustion air in a very short mixing section without separation areas and with a uniform speed profile, which is a prerequisite for minimization is the NOx content and, on the other hand, due to the residual vortex generated by the vortex generators, which is still present after mixing in the fuel / air mixture flow, the recirculation zone is positively influenced, which increases the flame stability and the cross-mixing of the various burners improved in an annular combustion chamber.
  • the ring-shaped premix burner according to the invention is furthermore distinguished by a simple geometry and is therefore structurally easy to manufacture.
  • the inner cylinder To form the recirculation zone, which serves as an ignition source for incoming fresh fuel / air mixture, it is also necessary for the inner cylinder to close after a sufficient length of the annular premixing section. This can expediently take place gradually or abruptly, so that the main flow channel either widens gradually or there is a sudden transition from the ring channel to the circular channel.
  • the recirculation zone then forms in a circular cross section.
  • vortex generators are advantageously arranged in the premix burner, which have approximately the shape of a right-angled triangle of small thickness, the two triangular side surfaces flowed parallel to one another and together with the roof surface comprising the connecting surface, the roof surface with an edge and the connecting surface with one edge touch the same duct wall as the two side walls.
  • FIG. 1 shows in a longitudinal section a possible embodiment of the annular premix burner according to the invention. It essentially consists of two cylinders with each other of different diameters, which are arranged concentrically to one another, so that the inner cylinder wall 21a and the outer cylinder wall 21b delimit an annular channel 20. Vortex generators 9 are arranged in the inlet area of the channel 20, the shape and mode of operation of which are described below.
  • the channel 20 has a constant height H and, downstream of the vortex generators, has a length L which lies in the range between 5 to 20 times its height H and forms the premixing section for combustion air 1 and gaseous fuel 2.
  • gaseous fuel 2 is injected via pipes 3 via openings 4 in the outer cylinder wall 21b as a secondary flow into the main flow of the ring channel 20 and mixed with the combustion air 1.
  • the introduction of the gaseous fuel 2 could of course also take place on the inner cylinder wall 21a or best on both walls 21a and 21b, as shown in the lower part of FIG. 1.
  • the inner cylinder wall 21a closes gradually after the premixing section, so that the inner cylinder is closed off by a cone tip.
  • the outer cylinder wall 21b initially also narrows in the area of the cone tip before it then encloses a circular cross section in which a recirculation zone is formed, which serves as an ignition source for incoming fresh fuel / air mixture.
  • FIG. 2 shows a further embodiment variant of the annular premix burner.
  • the inner cylinder suddenly closes here after a sufficiently long premixing section (length L is approximately 5 to 20 times the channel height H), so that the transition from the ring channel 20 to the circular channel in which the Recirculation zone 22 forms, takes place abruptly.
  • the gaseous fuel 2 is in this case through openings on the inner and outer cylinders directly downstream of the vortex generators 9, annular fuel supply lines 5 are introduced as a secondary flow into the main flow swirled by the vortex generators and mixed intensively with the air.
  • vortex generators 9 are also arranged in the annular channel 20, via which the air 1 is guided and swirled as the main flow before gaseous fuel is injected immediately downstream of the vortex generators 9.
  • 9 deflection vanes 8 are arranged in the annular channel 20 upstream of the vortex generators. The same effect can be achieved if the main flow enters the annular space into the annular space 20 via tangential slots (not shown here) and thereby receives a tangential velocity component.
  • the inner cylinder also closes gradually here, but not to a cone tip, but to a hemisphere.
  • lines 6 are arranged for the supply of liquid fuel 7, which is injected into the circular cross section of the burner at the end of the premixing section for the combustion air 1 and the gaseous fuel 2 from nozzles arranged in the hemispherical end of the inner cylinder.
  • liquid fuel 7 can also be introduced, for example via a fuel lance, and mixed with the air swirled by the vortex generators in the annular space 20.
  • the vortex generators 9 installed in the ring channel 20 can have different shapes. It is essential for the invention that they produce longitudinal vortices without a recirculation area and thereby enable a complete mixing of the fuel with the combustion air within a very short distance, on the other hand after the mixing a residual vortex remains in the flow, which is present along the wake of the inner cylinder. This residual vortex influences the recirculation zone and ensures high flame stability on the one hand and good cross-mixing of the various burners in the ring combustion chamber on the other.
  • the vortex generators 9 shown schematically in the above exemplary embodiments are half delta wings, i.e. (see FIG. 4) that a vortex generator 9 has three freely flowing surfaces 10, 11, 12, which extend in the direction of flow and one of which forms the roof surface 10 and the other two the side surfaces 11, 13, that the side surfaces 11 , 13 are flush with the same channel wall 21 and one side surface 11 is provided with an arrow angle ⁇ / 2, while the other side surface 13 is straight and oriented in the flow direction, that the roof surface 10 with an edge 15 running transversely to the channel 20 through which flow flows same channel wall 21 as the side surfaces 11, 13, and that the longitudinal edges 12, 14 of the roof surface 10, which are flush with the longitudinal edges of the side surfaces 11, 13 projecting into the flow channel 21, extend at an angle of attack ⁇ to the channel wall 21.
  • the two side surfaces 11, 13 comprise a connecting edge 16 with one another which, together with the longitudinal edges 12, 14 of the roof surface 10, forms a tip 18, the connecting edge running in the radial direction of the curved channel wall 21.
  • the connecting edge 16 and / or the longitudinal edges 12, 14 of the roof surface 10 are at least approximately sharp.
  • the connecting edge 16 of the vortex generators 9 described in FIG. 4 forms the downstream edge of the vortex generator 9 and the edge 15 of the roof surface 10 which runs transversely to the channel 20 through which flow flows is the edge first acted upon by the main flow because the vortex can build up particularly well.
  • the vortex generator works as follows: When flowing around the edge 14 of the side surface 11 provided with the half arrow angle ⁇ / 2, the main flow is converted into a vortex, the axis of which lies in the axis of the main flow. No swirl is generated on the straight side surface 13, which is oriented in the direction of flow of the main flow, so that a swirl is forced on the flow and no swirl-neutral field is present. If the fuel is introduced into the main flow as a secondary flow immediately downstream of the vortex generators 9, the combustion air 1 and the fuel 2 are mixed intensively.
  • the vortex generator 9a has approximately the shape of a right-angled triangle of small thickness, the two triangular side surfaces 11, 13 around which flow flows parallel to one another and together with the roof surface 10 comprise the connection surface 19, the roof surface 10 with an edge 15 and the connection surface 19 rest with an edge 17 on the same duct wall as the two side walls 11, 13 and the side surfaces 11, 13 form an angle ⁇ with the main flow direction of the incoming air.
  • the roof surface 10 can also be concave or convex curved. In comparison to vortex generators 9a with a straight roof surface, this has the advantage that the same vortex strength is generated with a lower pressure drop can.
  • vortex generators 9a Another advantage of the vortex generators 9a is that they can be manufactured extremely simply, for example by punching out thin sheets. Since the width of the roof surface 10 in the vortex generators 9a is extremely small, the vortex formation practically only occurs on one side and a very large vortex is formed which has a positive influence on the fuel / air mixture formation.
  • FIG. 6 shows a modified embodiment of the vortex generator 9a shown in FIG. 5, in which the two side surfaces 11 and 13 do not have the shape of a right-angled triangle, but are trapezoidal. These vortex generators 9a are also outstandingly suitable for generating vortexes.
  • FIGS. 7 to 10 show different arrangement variants of the vortex generators 9 and 9a in the ring channel 20 of the premix burner.
  • vortex generators 9 are arranged both on the inner cylinder wall 21a and on the outer cylinder wall 21b. They have a height h that fills almost the entire duct height H.
  • the vortex generators 9, which are arranged on the inner cylinder wall 21a, are smaller than those arranged on the outer wall 21b, their height h is only approximately H / 2, while the height h of the outer vortex generators 9 is equal to the channel height H.
  • the use of vortex generators 9 of different geometry creates vortices of different strengths, which has a favorable effect on the residual vortices required for flame stabilization.
  • FIG. 9 shows an arrangement of vortex generators 9a with a geometry according to FIG. 6. Their height h corresponds to the channel height H, ie they fill the entire channel height H. Of the flattened part of the roof surface 13 adjoins the inner cylinder wall 21a. The resulting vortices are marked with arrows.
  • FIG. 10 shows an arrangement variant of the vortex generators 9a according to FIG. 5 in the ring channel 20.
  • the vortex generators 9a are arranged on the inner cylinder wall 21a as well as on the outer cylinder wall 21b, for example welded on.
  • Two opposite vortex generators 9a are each offset by half a pitch to one another in the circumferential direction, so that the swirl direction outside and inside is the same and the vortexes add up as desired to form a large vortex that is both sufficient for the complete mixing of air and fuel also subsequently contributes to flame stabilization as a residual vortex.
  • the premix burner is also ideally suited for operation at partial load because the geometry of the burner makes it easy to inject pilot gas or secondary gas directly into the recirculation zone. This increases the stability limit of the burner.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP96810756A 1995-11-23 1996-11-07 Brûleur à prémélange Expired - Lifetime EP0775869B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19543701A DE19543701A1 (de) 1995-11-23 1995-11-23 Vormischbrenner
DE19543701 1995-11-23

Publications (3)

Publication Number Publication Date
EP0775869A2 true EP0775869A2 (fr) 1997-05-28
EP0775869A3 EP0775869A3 (fr) 1998-03-11
EP0775869B1 EP0775869B1 (fr) 2001-09-05

Family

ID=7778238

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810756A Expired - Lifetime EP0775869B1 (fr) 1995-11-23 1996-11-07 Brûleur à prémélange

Country Status (4)

Country Link
US (1) US5791892A (fr)
EP (1) EP0775869B1 (fr)
JP (1) JPH09170729A (fr)
DE (2) DE19543701A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003098110A1 (fr) * 2002-05-16 2003-11-27 Alstom Technology Ltd Bruleur a premelange
DE10250208A1 (de) * 2002-10-28 2004-06-03 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
CN102853426A (zh) * 2012-09-29 2013-01-02 宋涛 预混式合金纤维灶头
WO2018122574A1 (fr) * 2016-12-29 2018-07-05 I.C.I. Caldaie S.P.A. Chaudière de production d'eau chaude ou de vapeur
EP3889506A1 (fr) * 2020-03-31 2021-10-06 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant
WO2021197654A1 (fr) 2020-03-31 2021-10-07 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur, et brûleur d'une turbine à gaz présentant un composant de brûleur de ce type

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EP0924459A1 (fr) * 1997-12-17 1999-06-23 Asea Brown Boveri AG Procédé et dispositif pour l'injection d'un mélange de carburant et de liquide dans une chambre de combustion
US6672862B2 (en) 2000-03-24 2004-01-06 North American Manufacturing Company Premix burner with integral mixers and supplementary burner system
US7520272B2 (en) * 2006-01-24 2009-04-21 General Electric Company Fuel injector
US20070249738A1 (en) * 2006-04-25 2007-10-25 Haynes Joel M Premixed partial oxidation syngas generator
US8795041B2 (en) * 2006-11-28 2014-08-05 Shimadzu Corporation Conditioned air supply method and supply system for aircraft
US20080302351A1 (en) * 2007-06-06 2008-12-11 Hunter Donald O Gas-Fired Portable Heater
KR100988836B1 (ko) * 2008-05-16 2010-10-20 이재랑 업소용 가스버너
AU2012214774A1 (en) * 2011-01-20 2013-08-22 Cascade Designs, Inc. Combined fuel and oxidizer metering jets, systems, and methods for simultaneously metering fuel and oxidizer
US9285120B2 (en) 2012-10-06 2016-03-15 Coorstek, Inc. Igniter shield device and methods associated therewith
EP2725302A1 (fr) * 2012-10-25 2014-04-30 Alstom Technology Ltd Agencement de brûleur de postcombustion
WO2015134009A1 (fr) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Moteur à turbine à gaz avec système de mélange statique de flux d'échappement de compresseur
US10222059B2 (en) * 2016-08-16 2019-03-05 Preferred Utilities Manufacturing Corporation Apparatus for reducing emissions when burning various fuels
RU181834U1 (ru) * 2018-04-24 2018-07-26 Виктор Николаевич Бирюков Устройство для сжигания газа
CN117881926A (zh) * 2021-08-31 2024-04-12 安曼瑞士股份公司 特别是用于沥青搅拌机的干燥筒的燃气的燃烧器

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EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0619456A1 (fr) 1993-04-08 1994-10-12 ABB Management AG Système d'alimentation en carburant pour chambre de combustion

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Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0619456A1 (fr) 1993-04-08 1994-10-12 ABB Management AG Système d'alimentation en carburant pour chambre de combustion

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003098110A1 (fr) * 2002-05-16 2003-11-27 Alstom Technology Ltd Bruleur a premelange
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
DE10250208A1 (de) * 2002-10-28 2004-06-03 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
DE10250208A9 (de) * 2002-10-28 2004-12-23 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
CN102853426A (zh) * 2012-09-29 2013-01-02 宋涛 预混式合金纤维灶头
CN102853426B (zh) * 2012-09-29 2014-11-26 宋涛 预混式合金纤维灶头
WO2018122574A1 (fr) * 2016-12-29 2018-07-05 I.C.I. Caldaie S.P.A. Chaudière de production d'eau chaude ou de vapeur
EP3889506A1 (fr) * 2020-03-31 2021-10-06 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant
WO2021197654A1 (fr) 2020-03-31 2021-10-07 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur, et brûleur d'une turbine à gaz présentant un composant de brûleur de ce type
US12050012B2 (en) 2020-03-31 2024-07-30 Siemens Energy Global GmbH & Co. KG Burner component of a burner, and burner of a gas turbine having a burner component of this type

Also Published As

Publication number Publication date
DE59607621D1 (de) 2001-10-11
US5791892A (en) 1998-08-11
EP0775869A3 (fr) 1998-03-11
EP0775869B1 (fr) 2001-09-05
DE19543701A1 (de) 1997-05-28
JPH09170729A (ja) 1997-06-30

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