EP0786626A1 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

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Publication number
EP0786626A1
EP0786626A1 EP96810849A EP96810849A EP0786626A1 EP 0786626 A1 EP0786626 A1 EP 0786626A1 EP 96810849 A EP96810849 A EP 96810849A EP 96810849 A EP96810849 A EP 96810849A EP 0786626 A1 EP0786626 A1 EP 0786626A1
Authority
EP
European Patent Office
Prior art keywords
fuel
premix burner
partial shells
flow
burner according
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Withdrawn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
EP96810849A
Other languages
German (de)
English (en)
Inventor
Hans Peter
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 Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0786626A1 publication Critical patent/EP0786626A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D5/00—Burners in which liquid fuel evaporates in the combustion space, with or without chemical conversion of evaporated fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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 present invention relates to a premix burner according to the preamble of claim 1.
  • a premix burner which, designed as a swirl burner, consists of at least two conical partial shells nested one inside the other in the flow direction, the respective cone axis of which is offset with respect to a burner axis and parallel to one another such that the adjacent walls of the conical partial shells form tangential channels or air inlet slots in the longitudinal extension thereof for the flow of a combustion air flow into the interior of the premix burner.
  • the premix burner On the head side, has a nozzle which is arranged essentially on the burner axis and is preferably operated with a liquid fuel.
  • the combustion air flowing tangentially into the interior of the premix burner detects the conical fuel spray released by the nozzle, whereupon a fuel / air mixture is formed.
  • a flame front with a stabilized backflow zone or backflow bubble forms in the area of the outlet of the premix burner.
  • further nozzles are arranged in the longitudinal direction, which are preferably operated with a gaseous fuel.
  • a fuel line extends along the tangential air inlet slots, which is preferably expanded with the nozzles mentioned. This fuel line is preferably welded to the conical partial shell in the axial direction by sector.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object in a premix burner of the type mentioned Kind of providing the formation of the fuel line in such a way that no uncontrolled flow conditions arise in this area during operation.
  • the object is achieved in that the conical partial shell and the fuel line consist of a single piece.
  • the fuel line is formed by bending the sheet around the conical partial shell, the end then being welded to the outer surface of the conical partial shell.
  • the main advantage of the invention can be seen in the fact that there is no welded connection between two different bodies in the region of the tangential air inlet slots, where the inflow of the combustion air takes place. Because the shell and fuel line are made in one piece, there is no longer any inherent risk of an uncontrolled flow through the gaps forming in the area of the weld.
  • Another advantage of the invention is that the holes that form the fuel nozzles can be made in advance of the formation of the fuel line with optimal machining conditions and machining methods.
  • FIGS. 2 and 3 are used simultaneously with FIG. 1.
  • the burner 100 according to FIG. 1 is a premix burner and consists of two conical partial shells 101, 102 which are nested one inside the other offset.
  • the offset of the respective central axis or longitudinal symmetry axes 101b, 102b of the conical partial shells 101, 102 to one another creates a tangential air inlet slot 119, 120 on both sides, in a mirror-image arrangement (FIGS. 2, 3), through which a combustion air 115 enters the interior of the Premix burner 100, ie into the cone cavity 114 flows.
  • the conical shape of the partial shells 101, 102 shown in the flow direction has a certain fixed angle.
  • the conical partial shells 101, 102 can have an increasing or decreasing cone inclination in the flow direction, similar to a diffuser or confuser. The last two forms are not included in the drawing, since they can be easily understood by a person skilled in the art.
  • the two conical partial shells 101, 102 each have a cylindrical initial part 101a, 102a, which, similarly to the conical partial shells 101, 102, also run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the premix burner 100.
  • a nozzle 103 is accommodated, the injection 104 of which coincides approximately with the narrowest cross section of the conical cavity 114 formed by the conical partial shells 101, 102.
  • the injection capacity and the type of this nozzle 103 depend on the predetermined parameters of the respective premix burner 100.
  • the premix burner can consist of purely tapered partial shells, that is to say without a cylindrical initial part, as can be seen from FIG. 1.
  • the conical partial shells 101, 102 also each have a fuel line 108, 109, which runs along the tangential air inlet slots 119, 120 and are provided with injection openings 117, through which a gaseous fuel 113 is preferably injected into the combustion air 115 flowing through it, such as arrows 116 symbolize this.
  • These fuel lines 108, 109 are to be arranged in the region of the tangential air inlet slots in such a way that an optimal air / fuel mixture can be achieved.
  • the detailed embodiments of these fuel lines 108, 109 are discussed in more detail below.
  • the outlet opening of the premix burner 100 merges into a front wall 110, in which a number of bores 110a are provided.
  • the latter come into operation when necessary and ensure that dilution air or cooling air 110 b is supplied to the front part of the combustion chamber 122.
  • this air supply ensures flame stabilization at the outlet of the premix burner 100. This flame stabilization becomes important when it comes to supporting the compactness of the flame due to a radial flattening.
  • the fuel brought in through the nozzle 103 is a liquid fuel 112, which can be enriched with a recirculated exhaust gas at most. This fuel 112 is injected into the cone cavity 114 at an acute angle.
  • a conical fuel profile 105 is thus formed from the nozzle 103 and is enclosed by the rotating combustion air 115 flowing in tangentially.
  • the concentration of the fuel 112 is continuously reduced to an optimal mixing by the incoming combustion air 115.
  • the position of the fuel nozzle 103 on the burner axis can be shifted upstream by a defined distance compared to the narrowest cross section of the conical partial shells 101, 102. This depends on the compactness of the fuel spray 105, which must already be penetrated by the incoming combustion air 115 on the head side of the premix burner 100 in order to be able to produce an optimal mixture. If the premix burner 100 is operated with a gaseous fuel 113, this is preferably done via opening nozzles 117, the formation of this fuel / air mixture taking place directly at the end of the air inlet slots 119, 120.
  • the optimal, homogeneous fuel concentration over the cross section is achieved in the region of the vortex run, that is to say in the region of the backflow zone 106 at the end of the premix burner 100.
  • the ignition takes place at the tip of the backflow zone 106. Only at this point can a stable flame front 107 arise.
  • a flashback of the flame into the interior of the premix burner 100 as is latently the case with known premix sections There is no need to worry about what is being sought there with complicated flame holders.
  • the combustion air 115 is additionally preheated or enriched with a recirculated exhaust gas, this supports the evaporation of the liquid fuel 112 before the combustion zone is reached.
  • the axial speed within the premix burner 100 can be changed by a corresponding supply, not shown, of an axial combustion air flow.
  • the design of the premix burner 100 is furthermore excellently suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operating range can be recorded without changing the overall length of the premix burner 100.
  • the individual conical partial shells 101, 102 can also be interconnected in a spiral manner.
  • the geometric configuration of the fuel lines 108, 109 is now apparent from FIG. 2. These are formed from the corresponding partial shells 101, 102 in one piece by continuously bending their ends and welding them onto the outer surface of the respective partial shell.
  • the fuel nozzles 117 are located directly in the region of the tangential air inlet slots 119, 120, through which the combustion air 115 flows into the cone cavity 114. In this area, the inflow of the combustion air 115 remains free of interferences which are harmful to the flow, because the fuel lines 108, 109 are not subject to any calorific-related distortions with respect to the partial shells.
  • the homogeneity when the combustion air 115 flows into the cone cavity 114 results in an optimal mixture formation with the fuel injection 116 taking place there. With such a configuration, the fuel lines can also be drawn upstream via the tangential air inlet slots 119, 120, like the dashed body 109a in FIG. 2 shows.
  • the fuel nozzles 117a can also be arranged above the tangential air inlet slots 119, 120 as required. These can have an oblique fuel injection 116a, such that the fuel jet flows past the edge of the opposite partial shell 101, which triggers at least one cooling effect.
  • Another advantage of this design is the possibility of extending the mixing section, which results in an improvement in the mixing with a concomitant reduction in pollutant emissions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Gas Burners (AREA)
EP96810849A 1995-12-27 1996-12-05 Brûleur à prémélange Withdrawn EP0786626A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19548851 1995-12-27
DE19548851A DE19548851A1 (de) 1995-12-27 1995-12-27 Vormischbrenner

Publications (1)

Publication Number Publication Date
EP0786626A1 true EP0786626A1 (fr) 1997-07-30

Family

ID=7781502

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810849A Withdrawn EP0786626A1 (fr) 1995-12-27 1996-12-05 Brûleur à prémélange

Country Status (5)

Country Link
EP (1) EP0786626A1 (fr)
JP (1) JPH09189405A (fr)
KR (1) KR970046925A (fr)
CA (1) CA2192741A1 (fr)
DE (1) DE19548851A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018005192B3 (de) 2018-07-02 2019-12-05 Truma Gerätetechnik GmbH & Co. KG Brennervorrichtung
CN115435324A (zh) * 2022-11-04 2022-12-06 佛山市德力泰科技有限公司 防止回火的多燃料混合装置及燃烧器

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59709791D1 (de) * 1997-09-19 2003-05-15 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
ATE244380T1 (de) * 1997-11-21 2003-07-15 Alstom Brenner für den betrieb eines wärmeerzeugers
KR100361976B1 (ko) * 1999-09-15 2002-11-25 오창선 고점도 연료용 연소버너

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0210462A1 (fr) * 1985-07-30 1987-02-04 BBC Brown Boveri AG Chambre de combustion double
WO1993017279A1 (fr) * 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
EP0641971A2 (fr) * 1993-09-06 1995-03-08 Abb Research Ltd. Procédé pour commander un brûleur à prémélange
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
EP0694730A2 (fr) * 1994-07-25 1996-01-31 Abb Research Ltd. Bruleur

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3819899C1 (en) * 1988-06-11 1989-11-30 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Apparatus for generating a homogeneous mixture from a first and second medium
CH680157A5 (fr) * 1989-12-01 1992-06-30 Asea Brown Boveri
CH687831A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Vormischbrenner.
SE9304194L (sv) * 1993-12-17 1995-06-18 Abb Stal Ab Bränslespridare

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0210462A1 (fr) * 1985-07-30 1987-02-04 BBC Brown Boveri AG Chambre de combustion double
WO1993017279A1 (fr) * 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
EP0641971A2 (fr) * 1993-09-06 1995-03-08 Abb Research Ltd. Procédé pour commander un brûleur à prémélange
EP0694730A2 (fr) * 1994-07-25 1996-01-31 Abb Research Ltd. Bruleur
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018005192B3 (de) 2018-07-02 2019-12-05 Truma Gerätetechnik GmbH & Co. KG Brennervorrichtung
CN115435324A (zh) * 2022-11-04 2022-12-06 佛山市德力泰科技有限公司 防止回火的多燃料混合装置及燃烧器

Also Published As

Publication number Publication date
CA2192741A1 (fr) 1997-06-28
DE19548851A1 (de) 1997-07-03
JPH09189405A (ja) 1997-07-22
KR970046925A (ko) 1997-07-26

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