EP0727611A1 - Chambre de combustion avec combustion en deux étages - Google Patents

Chambre de combustion avec combustion en deux étages Download PDF

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Publication number
EP0727611A1
EP0727611A1 EP96810072A EP96810072A EP0727611A1 EP 0727611 A1 EP0727611 A1 EP 0727611A1 EP 96810072 A EP96810072 A EP 96810072A EP 96810072 A EP96810072 A EP 96810072A EP 0727611 A1 EP0727611 A1 EP 0727611A1
Authority
EP
European Patent Office
Prior art keywords
burner
combustion chamber
combustion
primary
fuel
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Withdrawn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
EP96810072A
Other languages
German (de)
English (en)
Inventor
Rolf Dr. Althaus
Jakob J. Prof. Dr. Keller
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 AG Germany
Original Assignee
ABB Management AG
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 Management AG filed Critical ABB Management AG
Publication of EP0727611A1 publication Critical patent/EP0727611A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • F23C6/047—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure with fuel supply in stages
    • 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 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • 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 
    • F23C2201/00—Staged combustion
    • F23C2201/10—Furnace staging
    • 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 combustion chamber with two-stage combustion, with at least one primary burner of the premix type, in which the fuel injected via nozzles is intensively mixed with the combustion air prior to ignition within a premixing chamber, and with at least one secondary burner which is arranged downstream of a pre-combustion chamber.
  • the single-stage combustion chambers with premix burners have the inadequacy that, at least in the operating states in which only some of the burners are operated with fuel, or in which the individual burners are supplied with a reduced amount of fuel, the flame stability is pushed close to the limit . In fact, due to the very lean mixture and the resulting low flame temperature under typical gas turbine conditions, the extinguishing limit is already reached with an excess air ratio of approximately 2.0.
  • the invention tries to avoid all these disadvantages. It is particularly based on the task of creating low-emission secondary combustion.
  • the primary burner is a flame-stabilizing premix burner without a mechanical flame holder, with at least approximately tangential inflow of the combustion air into the premixing chamber, and in that the secondary burner is a non-self-sufficient premix burner.
  • Such flame-holding premix burners can be, for example, the burners of the so-called double-cone type, as are known from EP-B1-0 321 809 and are described later in relation to FIGS. 1 to 3B.
  • the fuel, there gas, is injected in the tangential inlet gaps into the combustion air flowing in from the compressor via a series of injector nozzles. As a rule, these are evenly distributed over the entire column.
  • the advantage of the invention can be seen in particular in a NO x -neutral secondary combustion.
  • the control can also be simplified insofar as the combustion chamber is loaded and unloaded, it is possible to cross air ratio ranges which, as a rule, could not be traversed with the previous premix combustion without using separate means extinguishing the flame must be avoided.
  • Fig. 1 50 is a jacketed plenum, which generally receives the combustion air delivered by a compressor, not shown, and supplies it to an annular combustion chamber 60.
  • This combustion chamber is designed in two stages and essentially consists of a pre-combustion chamber 61 and a downstream main combustion chamber 62, both of which are encased with a combustion chamber wall 63.
  • An annular dome 55 is placed on the pre-combustion chamber 62, which is located at the head end of the combustion chamber 60 and whose combustion chamber is delimited by a front plate 54.
  • a burner 110 is arranged in this dome in such a way that the burner outlet is at least approximately flush with the front plate 54.
  • the longitudinal axis 51 of the primary burner 110 runs coaxially with the longitudinal axis 52 of the combustion chamber 60.
  • a plurality of such burners 110 are distributed next to one another over the circumference the annular front plate 52 arranged (Fig.2).
  • the combustion air flows from the plenum 50 into the interior of the dome and acts on the burners via the dome wall perforated at its outer end.
  • the fuel is fed to the burner via a fuel lance 120 which penetrates the dome and plenum walls.
  • a number of secondary burners 150 are arranged in the plane in which the pre-combustion chamber 61 merges into the main combustion chamber 62. These are also premix burners. Its longitudinal axis 53 runs perpendicular to the longitudinal axis of the primary burner 110.
  • These secondary burners also sit on a front plate 74 and are surrounded by an annular dome 75.
  • the burner 150 is arranged in this dome in such a way that the burner outlet 158 is at least approximately flush with the front plate 74.
  • a plurality of such burners 150 are arranged next to one another on the annular front plate 74 distributed over the circumference (FIG. 2).
  • the combustion air flows from the plenum 50 into the interior of the dome and acts on the burners via the dome wall perforated at its outer end.
  • the fuel is fed to the burner via a fuel lance 121 which penetrates the dome and plenum walls.
  • the distance between the secondary burners and the exit plane 118 of the primary burners is approximately one burner diameter.
  • the Exit plane 158 of the secondary burner is set back with respect to combustion chamber wall 64.
  • an equal number, here 30 pieces, of primary burners 110 and secondary burners 150 are arranged over the circumference, their axes being offset by half a division in the circumferential direction.
  • this number and arrangement is not mandatory.
  • the premix burners 110 and 150 shown schematically in FIGS. 1, 2, 3A and 3B are each a so-called double-cone burner, as was already mentioned above and is known, for example, from EP-B1-0 321 809. It essentially consists of two hollow, conical partial bodies 111, 112 which are nested one inside the other in the direction of flow. The respective central axes 113, 114 of the two partial bodies are offset from one another. The adjacent walls of the two partial bodies in their longitudinal extent form tangential slots 119 for the combustion air, which in this way reaches the interior of the burner. A first fuel nozzle 116 for liquid fuel is arranged there. The fuel is injected into the hollow cone at an acute angle.
  • the resulting conical fuel profile is enclosed by the combustion air flowing in tangentially.
  • the concentration of the fuel is continuously reduced in the axial direction due to the mixing with the combustion air.
  • the burner is also operated with gaseous fuel.
  • gas inflow openings 117 distributed in the longitudinal direction are provided in the region of the tangential slots 119 in the walls of the two partial bodies. In gas operation, the mixture formation with the combustion air thus already begins in the zone of the inlet slots 119. It goes without saying that mixed operation with both types of fuel is also possible in this way.
  • a fuel concentration that is as homogeneous as possible is established over the applied annular cross section.
  • a defined dome-shaped recirculation zone 121 is formed, at the tip of which the ignition takes place. The flame itself is stabilized by the recirculation zone in front of the burner without the need for a mechanical flame holder.
  • the secondary burner 150 should now be a non-self-operating premix burner. This is understood to mean that permanent ignition must be present for the mixture combustion of the secondary burner. In the present case, this permanent ignition takes place via the flame at the outlet of the pre-combustion chamber.
  • the tangential gaps 119, 159 in the burners are dimensioned such that the primary burners, for example, are charged with approximately 25% and the secondary burners with approximately 75% of the total volume flow consisting of combustion air and fuel.
  • Such a combustion chamber can be operated as follows: only the primary burners 110 are operated for starting and kept in operation throughout the load range. From approx. 10% load up to full load, the secondary burners 150 are exposed to fuel.
  • the first turbine vane row is designated by 64.
  • the effect of the new measure is as follows: On the occasion of the pre-combustion, as a result of the distribution of the entire volume flow between primary burners and secondary burners, only part of the volume flow is produced because of the temperature increase ⁇ T 1C . This partial flow has only a short residence time in the pre-combustion chamber 61 until it is mixed with the mixture from the secondary burners, which has a favorable effect on the NO x production.
  • the mixing temperature must not drop below the compression ignition temperature T SI .
  • the invention is not limited to the use of premix burners of the double-cone type shown. Rather, it can be used in all combustion chamber zones in which flame stabilization is generated by a prevailing air velocity field.
  • FIG. 4 As a further example of this, reference is made to the burner shown in FIG. 4.
  • all functionally identical elements are provided with the same reference numerals as in the burner according to FIGS. 1-3B.
  • the area of the premixing chamber 130 which flows through in the direction of the burner outlet is formed in this burner by a centrally arranged insert 131 in the form of a straight circular cone, the cone tip being in the region of the front plate plane. It goes without saying that the lateral surface of this cone can also be curved. Incidentally, this also applies to the course of the partial surfaces 111, 112 in the burners shown in FIGS. 1-3B.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP96810072A 1995-02-20 1996-02-05 Chambre de combustion avec combustion en deux étages Withdrawn EP0727611A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH48795 1995-02-20
CH487/95 1995-02-20
DE19510743A DE19510743A1 (de) 1995-02-20 1995-03-24 Brennkammer mit Zweistufenverbrennung

Publications (1)

Publication Number Publication Date
EP0727611A1 true EP0727611A1 (fr) 1996-08-21

Family

ID=25684712

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810072A Withdrawn EP0727611A1 (fr) 1995-02-20 1996-02-05 Chambre de combustion avec combustion en deux étages

Country Status (3)

Country Link
EP (1) EP0727611A1 (fr)
JP (1) JPH08247419A (fr)
DE (1) DE19510743A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0899506A3 (fr) * 1997-08-30 1999-06-16 Abb Research Ltd. Dispositif de combustion
EP1254699A1 (fr) * 2001-05-04 2002-11-06 Robert Bosch Gmbh Mélangeur pour gaz dans une pile à combustible
CN108916862A (zh) * 2018-09-12 2018-11-30 段景峰 一种生物质粉末可控湍流预混燃烧室及其使用方法
CN110160040A (zh) * 2019-01-08 2019-08-23 北京永博洁净科技有限公司 燃烧设备
EP3059498B1 (fr) * 2015-02-20 2020-10-21 United Technologies Corporation Mélangeur principal incliné pour chambre de combustion de stoechiométrie axialement contrôlée

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10056243A1 (de) 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
JP4670035B2 (ja) * 2004-06-25 2011-04-13 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器
US9423131B2 (en) * 2012-10-10 2016-08-23 General Electric Company Air management arrangement for a late lean injection combustor system and method of routing an airflow

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0281961A1 (fr) * 1987-03-06 1988-09-14 Hitachi, Ltd. Chambre de combustion pour turbine à gaz et méthode de combustion
EP0321809A1 (fr) * 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
EP0620362A1 (fr) * 1993-04-08 1994-10-19 ABB Management AG Turbine à gaz
GB2289326A (en) * 1994-05-11 1995-11-15 Abb Management Ag Combustion process for atmospheric combustion systems

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2629761A1 (de) * 1976-07-02 1978-01-05 Volkswagenwerk Ag Brennkammer fuer gasturbinen
EP0481111B1 (fr) * 1990-10-17 1995-06-28 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
DE59208831D1 (de) * 1992-06-29 1997-10-02 Abb Research Ltd Brennkammer einer Gasturbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0281961A1 (fr) * 1987-03-06 1988-09-14 Hitachi, Ltd. Chambre de combustion pour turbine à gaz et méthode de combustion
EP0321809A1 (fr) * 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
EP0620362A1 (fr) * 1993-04-08 1994-10-19 ABB Management AG Turbine à gaz
GB2289326A (en) * 1994-05-11 1995-11-15 Abb Management Ag Combustion process for atmospheric combustion systems

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0899506A3 (fr) * 1997-08-30 1999-06-16 Abb Research Ltd. Dispositif de combustion
EP1254699A1 (fr) * 2001-05-04 2002-11-06 Robert Bosch Gmbh Mélangeur pour gaz dans une pile à combustible
EP3059498B1 (fr) * 2015-02-20 2020-10-21 United Technologies Corporation Mélangeur principal incliné pour chambre de combustion de stoechiométrie axialement contrôlée
CN108916862A (zh) * 2018-09-12 2018-11-30 段景峰 一种生物质粉末可控湍流预混燃烧室及其使用方法
CN110160040A (zh) * 2019-01-08 2019-08-23 北京永博洁净科技有限公司 燃烧设备
CN110160040B (zh) * 2019-01-08 2024-05-31 北京永博洁净科技有限公司 燃烧设备

Also Published As

Publication number Publication date
DE19510743A1 (de) 1996-09-26
JPH08247419A (ja) 1996-09-27

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