EP0518072A1 - Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer - Google Patents

Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer Download PDF

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Publication number
EP0518072A1
EP0518072A1 EP92108152A EP92108152A EP0518072A1 EP 0518072 A1 EP0518072 A1 EP 0518072A1 EP 92108152 A EP92108152 A EP 92108152A EP 92108152 A EP92108152 A EP 92108152A EP 0518072 A1 EP0518072 A1 EP 0518072A1
Authority
EP
European Patent Office
Prior art keywords
burner
air inlet
nozzle
fuel
tangential air
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Withdrawn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
EP92108152A
Other languages
German (de)
English (en)
Inventor
Thomas Dr. Sattelmayer
Peter 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 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 EP0518072A1 publication Critical patent/EP0518072A1/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Withdrawn legal-status Critical Current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 
    • 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
    • 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
    • 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
    • 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 burner according to the preamble of claim 1.
  • Premix burners reach their best operating point with a precisely defined ratio of air volume and fuel volume. This point is close to the lean extinguishing limit.
  • the air distribution is generally chosen so that the optimum point is reached when the machine is under high load. If no special precautions are taken, the extinguishing limit will be exceeded even if the amount of fuel is moderately reduced.
  • the limit at which extinguishing occurs can be shifted towards the higher air excess by enriching the fuel concentration profile on the burner axis. This principle is generally known per se.
  • the ignition generally takes place in the vicinity of the fuel outlet bores.
  • the invention seeks to remedy this.
  • the object of the invention is to take precautions for a burner of the type mentioned at the outset, which have the effect that a high extinguishing limit is obtained regardless of the mass flow.
  • the main advantage of the invention is that another effect can be used to improve the deletion limit with simple means.
  • the aim is to specifically change the flow field so that as soon as a gaseous fuel is injected at the burner head, a core flame largely independent of the main flame can form on the axis. This results in the desired high extinguishing limit regardless of the mass flow. In terms of the device, this is achieved by supplementing the burner head with a second fuel injection for a gaseous fuel. The desired new effect is not achieved by this head step, but by closing a small part of the tangential air inlet slots.
  • Fig. 1 shows a schematic section through the burner, which consists essentially of two partial cone bodies 1, 2, the design of which can be seen particularly well in the following figures, which is why only a brief description is given here.
  • a central fuel nozzle 3 which, analogous to EP-A1-0 321 809, takes over the central feed on the burner head side, but now takes over a gaseous fuel.
  • Another Fuel supply affects the injection 16 via a line 8, which is located in the region of the tangential air inlet slots. This is also discussed in more detail in the following figures.
  • the burner is located upstream of a combustion chamber 22.
  • the postulated closures 24, 25 are clearly visible in FIG. 1, the effect of which is described in detail in the following figures.
  • FIG. 2 shows a perspective view of the burner, which has an integrated premixing zone per se.
  • the burner consists of two half hollow partial cone bodies 1, 2 which are radially offset from one another with respect to their longitudinal axis of symmetry. The offset of the respective longitudinal axis of symmetry 1b, 2b (Fig.
  • the two partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a, which, analogous to the partial cone bodies 1, 2, is offset run towards each other so that the tangential air inlet slots 19, 20 per se could be present continuously over the entire length of the burner. This is not the case here, because in the area of the central fuel nozzle 3 the above-mentioned tangential air inlet slots 19, 20 have been partially closed with closures 24, 25, the effect of which will still be explained.
  • this cylindrical initial part 1a, 2a the nozzle 3 is accommodated, the fuel injection 4 of which coincides approximately with the narrowest cross section of the conical cavity 14 formed by the two partial cone bodies 1, 2.
  • This nozzle 3 depends on the type of burner, ie whether it is, for example, a pilot burner or a main burner.
  • the burner can be of a purely conical design, that is to say it can be designed without a cylindrical starting part 1a, 2a.
  • Both partial cone bodies 1, 2 each have a fuel division 8, 9 in the region of the tangential air inlet slots 19, 20, which are provided on the long side with a number of openings 17 through which a gaseous and / or liquid fuel 13 flows, which in turn flows through the tangential ones Air inlet slots 19, 20 are mixed into the combustion air 15 flowing into the cone cavity 14, as the arrows 16 want to symbolize.
  • These fuel lines 8, 9 are preferably placed at the latest at the end of the tangential inflow, before entering the cone cavity 14, in order to obtain an optimal air / fuel mixture before the mixture enters the cone cavity 14.
  • Mixed operation with the two fuel feeds, that is to say once via the central nozzle 3 and once via the fuel line 8, 9, is of course possible.
  • the outlet opening of the burner merges into a front wall 10, in which a number of bores 10a are provided. The latter come into operation when necessary and ensure that dilution air or cooling air is supplied to the front part of the combustion chamber 22. In addition, this air supply ensures that flame stabilization takes place at the burner outlet.
  • the gaseous fuel 12 brought in through the nozzle is preferably injected into the cone cavity 14 through a plurality of openings 4, the fuel being injected at an acute angle with respect to the longitudinal axis of the burner.
  • the opening 4 are preferably arranged in a ring shape on the nozzle 4.
  • the tangential air inlet slots 19, 20 are closed in such a way that the flow field is specifically changed in such a way that as soon as fuel is injected into the burner head, ie through the nozzle 3, a core flame largely independent of the main flame 7 is generated the axis can form.
  • closures 24, 25 cover only a small part of the length of the tangential air inlet slots 19, 20, preferably 5-10%, the desired new effect is easily achieved, the exact axial placement of the closures 24, 25 in the region of the nozzle 3 is determined on a case-by-case basis.
  • a stable flame front 7 with a backflow zone 6 is established at the outlet of the burner.
  • a flashback of the flame into the interior of the burner as can potentially always be the case with the known premixing sections, while there is a remedy with complicated flame holders, there is no fear here.
  • the burner can be expanded in that the combustion air 15 is preheated, which is advantageous if, for example, a liquid fuel is passed over the lines 8, 9, since this would allow the fuel to be completely evaporated before the flame front 7 is reached.
  • exhaust gas recirculation could preferably be used.
  • the backflow zone 6, once fixed, is positionally stable because the swirl number increases in the direction of flow in the region of the cone shape of the burner.
  • the design of the burner is particularly suitable for changing the size of the tangential air inlet slots 19, 20 for a given overall length of the burner, this being provided by means which allow the partial cone bodies 1, 2 to be pushed towards or away from one another, whereby the distance between the two central axes 1b, 2b decreases or. increases, accordingly the gap size of the tangential air inlet slots 19, 20 changes, as can best be seen from FIGS. 3-5.
  • a spiral insertion of the two partial cone bodies 1, 2 into one another and their axial displacement relative to one another is also possible with certain combustion engineering orientations. It is therefore in your hand to vary the shape and size of the tangential air inlet slots 19, 20 as desired, with which the burner can be individually adjusted within a certain bandwidth without changing its overall length.
  • 3-5 shows the geometric configuration of the guide plates 21a, 21b. They have a flow introduction function, which, depending on their length, extend the respective end of the partial cone bodies 1, 2 in the direction of the flow relative to the combustion air 15.
  • the channeling of the combustion air 15 into the cone cavity 14 can be optimized by opening or closing the baffles 21a, 21b around a pivot point 23 located in the region of the entry of this channel into the cone cavity 14, in particular this is necessary if the original gap size of the tangential air inlet slots 19, 20 is changed.
  • these dynamic arrangements can also be provided statically, in that the required guide plates form a fixed component with the partial taper bodies 1, 2.
  • the burner can also be operated without baffles, or other aids can be provided for this.
  • 3 shows the closures 24, 25 attached on both sides, which close a certain length of the tangential air inlet slots 19, 20, in order to achieve the new effect described above in various ways.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP92108152A 1991-06-14 1992-05-14 Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer Withdrawn EP0518072A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1781/91 1991-06-14
CH178191 1991-06-14

Publications (1)

Publication Number Publication Date
EP0518072A1 true EP0518072A1 (fr) 1992-12-16

Family

ID=4218467

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92108152A Withdrawn EP0518072A1 (fr) 1991-06-14 1992-05-14 Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer

Country Status (3)

Country Link
EP (1) EP0518072A1 (fr)
JP (1) JPH05187638A (fr)
CA (1) CA2069718A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5375995A (en) * 1993-02-12 1994-12-27 Abb Research Ltd. Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation
EP0683219A2 (fr) * 1994-05-19 1995-11-22 Abb Research Ltd. Procédé de gazéification de combustibles carbonés à l'aide d'air soufflé
DE4426353A1 (de) * 1994-07-25 1996-02-01 Abb Research Ltd Brenner
EP0711953A2 (fr) * 1994-11-12 1996-05-15 Abb Research Ltd. Brûleur à prémélange
EP0718550A1 (fr) * 1994-12-19 1996-06-26 ABB Management AG Gicleur
EP0742411A2 (fr) * 1995-05-08 1996-11-13 ABB Management AG Alimentation en air pour une chambre de combustion à prémélange

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101235970B (zh) * 2007-01-31 2012-05-02 通用电气公司 具有逆流喷射装置的燃气轮机燃烧器

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH349018A (de) * 1959-07-01 1960-09-30 Seri Ag Brennereinrichtung für flüssige und gasförmige Brennstoffe
US3017920A (en) * 1959-02-26 1962-01-23 Eclipse Fuel Eng Co Ring burner with flame retention shield
DE2428622A1 (de) * 1973-06-15 1975-01-09 O F R Officine Fratelli Riello Brennerkopf, insbesondere fuer gasfoermige brennstoffe
EP0321809B1 (fr) * 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3017920A (en) * 1959-02-26 1962-01-23 Eclipse Fuel Eng Co Ring burner with flame retention shield
CH349018A (de) * 1959-07-01 1960-09-30 Seri Ag Brennereinrichtung für flüssige und gasförmige Brennstoffe
DE2428622A1 (de) * 1973-06-15 1975-01-09 O F R Officine Fratelli Riello Brennerkopf, insbesondere fuer gasfoermige brennstoffe
EP0321809B1 (fr) * 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5375995A (en) * 1993-02-12 1994-12-27 Abb Research Ltd. Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation
EP0683219A2 (fr) * 1994-05-19 1995-11-22 Abb Research Ltd. Procédé de gazéification de combustibles carbonés à l'aide d'air soufflé
EP0683219A3 (fr) * 1994-05-19 1996-01-10 Abb Research Ltd Procédé de gazéification de combustibles carbonés à l'aide d'air soufflé.
DE4426353A1 (de) * 1994-07-25 1996-02-01 Abb Research Ltd Brenner
US5562441A (en) * 1994-07-25 1996-10-08 Abb Research Ltd. Burner
EP0711953A2 (fr) * 1994-11-12 1996-05-15 Abb Research Ltd. Brûleur à prémélange
EP0711953A3 (fr) * 1994-11-12 1997-09-03 Abb Research Ltd Brûleur à prémélange
EP0718550A1 (fr) * 1994-12-19 1996-06-26 ABB Management AG Gicleur
EP0742411A2 (fr) * 1995-05-08 1996-11-13 ABB Management AG Alimentation en air pour une chambre de combustion à prémélange
DE19516798A1 (de) * 1995-05-08 1996-11-14 Abb Management Ag Vormischbrenner mit axialer oder radialer Luftzuströmung
US5738509A (en) * 1995-05-08 1998-04-14 Asea Brown Boveri Ag Premix burner having axial or radial air inflow
EP0742411A3 (fr) * 1995-05-08 1999-04-14 Asea Brown Boveri Ag Alimentation en air pour une chambre de combustion à prémélange

Also Published As

Publication number Publication date
CA2069718A1 (fr) 1992-12-15
JPH05187638A (ja) 1993-07-27

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