EP2171353A1 - Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange - Google Patents

Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange

Info

Publication number
EP2171353A1
EP2171353A1 EP08786350A EP08786350A EP2171353A1 EP 2171353 A1 EP2171353 A1 EP 2171353A1 EP 08786350 A EP08786350 A EP 08786350A EP 08786350 A EP08786350 A EP 08786350A EP 2171353 A1 EP2171353 A1 EP 2171353A1
Authority
EP
European Patent Office
Prior art keywords
fuel
injected
premixing zone
air
zone
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Withdrawn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
EP08786350A
Other languages
German (de)
English (en)
Inventor
Berthold Köstlin
Martin Lenze
Bernd Prade
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP08786350A priority Critical patent/EP2171353A1/fr
Publication of EP2171353A1 publication Critical patent/EP2171353A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • 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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07009—Injection of steam into the combustion chamber

Definitions

  • the present invention relates to a premix burner, in particular a synthesis gas premix burner, and a method of operating a premix burner.
  • Premix burners typically include a premix zone in which air and fuel are mixed before passing the mixture into a combustion chamber. There, the mixture burns, producing a hot gas under elevated pressure. This hot gas is forwarded to the turbine. In connection with the operation of premix burners, it is particularly important to keep the nitrogen oxide emissions low and to avoid a flashback.
  • Synthesis gas premix burners are characterized by the fact that synthesis gases are used as fuel in them. Compared with the traditional turbine fuels natural gas and petroleum, which consist essentially of hydrocarbon compounds, the combustible components of the synthesis gas are essentially carbon monoxide and hydrogen. Depending on the gasification process and the overall plant concept is the
  • Calorific value of the synthesis gas about 5 to 10 times smaller than that of natural gas.
  • Air at the flame front a significant factor to avoid temperature peaks and thus to minimize the thermal nitric oxide formation.
  • the main constituents of the synthesis gas are not only carbon monoxide and hydrogen but also inert fractions.
  • the inert fractions are nitrogen and / or water vapor and optionally carbon dioxide. Due to the low Heat value must therefore be introduced into the combustion chamber high volume flows of fuel gas. As a result, significantly larger injection cross sections are required for the combustion of low-calorie fuels, such as synthesis gases, than with conventional high-calorie combustion gases.
  • the air mass flow introduced into the combustion chamber is typically twisted by means of an air swirl generator.
  • the fuel is injected via one or more juxtaposed or successively arranged circular rows of holes.
  • EP 1 614 963 A1 proposes a method for reducing the nitrogen oxide emissions and for preventing flashbacks in the combustion of low-calorie fuels for the operation of a gas turbine, in which a low-calorie fuel is premixed with air in stages.
  • EP 1 614 967 A1 also proposes a method for burning a low-calorie fuel for the operation of a gas turbine, in which the low-calorie fuel is premixed with air to form a low-calorie fuel-air mixture as part of a premix and avoids conversion of the low-calorie fuel-air mixture becomes.
  • EP 1 507 120 A1 proposes a gas turbine with an annular combustion chamber, in which a swirl grating is arranged in a combustion air inlet region around the entire circumference of the annular combustion chamber, whereby a higher flow velocity of the incoming combustion air compared to individual Air inlet areas, each with a swirl grid is achieved. This results in a higher safety against flashbacks and a lower tendency to form combustion oscillations.
  • a flow separation or a return flow area within the premixing zone of the burner must be avoided at all costs. But at least potential return flow areas are to be designed in such a way that no damage to the burner takes place. As a rule, the backflow areas occur in near-wall zones in the wake of the fuel gas jets.
  • the method of the invention relates to a premix burner comprising a premix zone.
  • An air mass flow and fuel is injected into the combustion chamber, whereby a potential hot gas backflow region can form.
  • the method according to the invention is characterized in that a non-fuel-containing fluid is injected into the premixing zone downstream of the fuel injection.
  • the training selbiger Due to the local injection of, for example, cold air in the wake or remindström whiche the training selbiger is largely prevented within the Vormischzone of the burner. At least the fuel in these areas is diluted and cooled so far that no reaction or ignition of the fuel-air mixture can occur within the premixing zone of the burner. This allows a safe premix operation of the burner.
  • the fluid can be injected into the premixing zone along the surface of the premixing zone in the main flow direction in the potential hot gas backflow region. The injection of a fluid along the component surface in the main flow direction prevents the actual formation of the H thoroughlygas Wegström capablees and / or diluted and cools the local fuel-air mixture from such that no ignition conditions prevail.
  • the fuel can in particular be injected perpendicular to the main flow direction of the air mass flow in the premixing zone, which is advantageous in terms of a thorough mixing of air and fuel.
  • the fuel can be injected via at least one swirl blade into the premixing zone.
  • the fuel may in particular also be a synthesis gas.
  • the fluid injected into the premixing zone along the surface located in the potential hot gas return flow region can be, for example, air or an inert gas.
  • Inert gases are gases that are very slow to react, meaning they participate in only a few chemical reactions.
  • carbon dioxide, water vapor, nitrogen, but also all noble gases can be used as the inert gas.
  • the use of an inert gas is particularly suitable if ignition conditions for highly flammable fuels should be avoided.
  • air of the air mass flow which is in any case supplied to the premixing zone.
  • a proportion of 10% of the total air supplied to the premixing zone can be branched off and injected into it along the surface of the premixing zone located in the potential hot gas backflow region.
  • the proportion of for a long time the surface of the premixing zone located in the potential hot gas backflow region can be injected with air.
  • the height of the preferably used portion of the air depends on the geometry of the premixing zone, on the speed of the air mass flow and the speed of the injected fuel.
  • the premix burner of the present invention includes a premix zone, an air swirler with an air supply, and one or more fuel nozzles.
  • the fuel can be injected through the fuel nozzles into a mass air flow that is twisted by the air swirler in the premixing zone, whereby a potential hot gas backflow region can form.
  • the premix burner according to the invention is characterized in that the premix zone surface in the potential hot gas backflow region has at least one opening through which a fluid can be injected into the premix zone. In particular, there may be openings arranged so that the fluid can be injected in the main flow direction of the burner along the surface of the premixing zone.
  • the premix zone surface preferably has a plurality of openings in the hot gas backflow region.
  • Openings may advantageously be connected via a fluid channel to the air supply leading to the air swirler be that through the opening part of the air can be injected as fluid into the combustion chamber.
  • the fuel nozzles may be located on the cone side and / or on the hub side of the premix zone.
  • the fuel nozzles are arranged in one or more consecutive rows downstream of the air swirler. This allows a graduated fuel injection.
  • the fuel nozzles and / or the openings may be located in the air swirler, preferably in at least one swirl vane.
  • the individual fuel nozzles can be designed, for example, as round bores. Another possibility is to design the fuel nozzles so that the fuel can be injected perpendicular to the main flow direction of the air mass flow into the combustion chamber, which promotes the mixing. Of course, the fuel can be injected at any other angle to the air mass flow.
  • the fuel used may in particular be a synthesis gas.
  • Fig. 1 shows schematically a section through a part of a premix burner.
  • FIG. 2 shows schematically the flow conditions in the interior of the premix burner shown in FIG.
  • Fig. 3 shows schematically a section through a part of a premix burner according to the invention.
  • FIG. 4 shows schematically the flow conditions in the interior of the premix burner shown in FIG. Fig. 5 shows schematically a section through a swirl blade.
  • FIG. 1 schematically shows a section through a part of a conventional premix burner 1.
  • the premix burner 1 comprises inter alia a housing 7, a premix zone 2, an air swirler 10 and one or more fuel nozzles 11.
  • the premix zone 2 is radially symmetrical about the central axis 12 arranged.
  • the outer side of the premixing zone 2 seen from the center axis 12 is referred to below as the cone side 3.
  • the side of the premixing zone 2 facing the center axis 12 is referred to below as the hub side 4.
  • an air mass flow 5 reaches the air swirler 10.
  • the air swirler 10 swirls the air mass flow 5 and forwards it into the premixing zone 2. From there, the air mass flow in the main flow direction 9 to the combustion chamber (not shown) forwarded.
  • the fuel nozzles 11 direct fuel 6 into the premixing zone 2 perpendicularly to the main flow direction 9 of the air mass flow 5. Downstream of the fuel nozzle 11 in the main flow direction 9 now forms a H disclosegasgur- ström which 8 from. Instead of a vertical injection to the main flow direction 9 of the air mass flow 5, the fuel 6 can be injected at any other angle to the main flow direction 9.
  • the flow direction of the injected fuel is indicated by arrows 6, the flow direction of the supplied air mass flow is indicated by arrows 5.
  • the Main flow direction in the interior of the premixing zone 2 is marked by arrows 9.
  • FIG. 2 diagrammatically outlines the flow conditions in the interior of the premix zone 2.
  • FIG. 2 shows a plan view of the fuel nozzles 11 from the interior of the premixing zone 2.
  • the main flow direction of the air mass flow flowing past the fuel nozzles is indicated by arrows 9.
  • Downstream of the fuel nozzles 11 in the main flow direction 9 now form H thoroughlygas Wegströmge- areas 8 from.
  • the flow direction of the flowing back hot gas is indicated by arrows 13.
  • FIG. 3 schematically shows a section through a part of a premix burner 1 according to the invention.
  • the basic structure and principle of operation of the premix burner 1 shown in FIG. 3 substantially corresponds to that of the premix burner shown in FIG.
  • the premix burner according to the invention comprises one or more fluid inlet openings 14, which are located downstream of the fuel nozzle or nozzles 11 in the main flow direction 9.
  • the fluid inlet openings 14 open into the premixing zone 2.
  • a fluid for example air or an inert gas
  • the flow direction of the injected fluid is indicated by arrows 15. It runs within the premixing zone 2 substantially parallel to the main flow direction 9.
  • the immersed fluid prevents the formation of a hot gas return flow region, as occurs in the premix burner described in connection with FIG.
  • FIG. 4 the flow conditions in the interior of the premixing zone 2 shown in FIG. 3 are schematically sketched.
  • FIG. 4 shows a plan view of the fuel nozzles 11 and the fluid inlet openings 14 as seen from the premixing zone 2.
  • the main flow direction of the air flowing from the swirl generator 10 in the direction of the fuel nozzles 11 and the fluid inlet openings 14 is indicated by arrows 9.
  • the direction of flow of the fluid injected through the fluid inlet openings 14 is indicated by arrows 15.
  • the hot gas 13 is entrained in the main flow direction 9. A backflow of the hot gas 13 against the main flow direction 9 is effectively prevented in this way.
  • the fluid injected via the fluid inlet openings 14 is air which is connected to the air mass flow 5 via a fluid channel and branched off from it.
  • air With regard to the avoidance of the hot gas return flow, it has proved to be advantageous to supply about 5% to 20%, preferably 10%, of the total air supplied to the premix zone 2 via the fluid inlet openings 14 to the premix zone 2.
  • an inert gas for example carbon dioxide, water vapor or nitrogen, can alternatively be injected into the premixing zone 2 via the fluid inlet openings 14.
  • a noble gas is possible in principle.
  • the fuel can optionally be injected perpendicular to the main flow direction 9 of the air mass flow 5 in the premixing zone 2, as described in connection with Figure 1 and Figure 3, or the fuel can be injected at any angle to the main flow direction 9 of the air mass flow in the premixing zone 2.
  • the fuel nozzles 11 can be located both on the cone side 3 and on the hub side 4 of the premixing zone 2 or in the swirl blades 17. In the event that the fuel nozzles 11 are located on the cone side 3 of the premixing zone 2, it is advantageous to place the fluid inlet openings 14 correspondingly on the cone side 3 as well. The fluid inlet openings 14 should then turn into main flow be located downstream of the fuel nozzles 9 and allow injection of the fluid in the main flow direction 9.
  • the fuel nozzles 11 may be disposed in one or more rows one behind the other downstream of the air swirler 10. They can advantageously be designed as round holes.
  • the fuel injected by it may in particular also be a synthesis gas.
  • the swirl blade 17 has in its interior a fuel flow channel 18 and a fluid flow channel 19 located downstream of the main flow direction 9.
  • the fuel 6 is injected via the fuel flow channel 18 through fuel nozzles 11 from the swirl blade 17 into the premixing zone 2.
  • the fluid 15, which is preferably an inert gas, is injected via the fluid flow channel 19 through fluid inlet openings 20, 21, 22 into the premixing zone 2.
  • the fluid inlet openings 20, 21, 22 are in the main flow direction 9 downstream of the fuel nozzles 11.
  • a portion of the fluid 15 through fluid inlet openings 20, which are arranged downstream of the fuel nozzles 11, substantially opposite to the main flow direction 9 in the Premix zone 2 injected.
  • fluid inlet openings 21 arranged further downstream of the fluid inlet openings 20
  • part of the fluid 15 is injected into the premixing zone 2 almost perpendicular to the main flow direction 9.
  • Downstream of the fluid inlet openings 21, further fluid inlet openings 22 are arranged, through which a part of the fluid inlet openings 22 are arranged.
  • ids 15 is injected into the premixing zone 2 substantially in the main flow direction 9.
  • the described arrangement of the fluid inlet openings 20, 21, 22 avoids the formation of a hot gas return region downstream of the fuel nozzles 11, thus enabling a safe premixing operation of the burner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

La présente invention concerne un procédé de fonctionnement d'un brûleur à prémélange (1). Le brûleur à prémélange ((1) comporte une zone de prémélange (2). Un courant de masse d'air (5) et un combustible (6) peuvent être injectés dans la zone de prémélange (2), une zone de reflux d'air chaud potentielle (8) pouvant se former. Le procédé selon l'invention est caractérisé en ce qu'un fluide ne contenant pas de combustible (15) est injecté en aval de l'injection de combustible dans la zone de prémélange (2).
EP08786350A 2007-07-27 2008-07-23 Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange Withdrawn EP2171353A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08786350A EP2171353A1 (fr) 2007-07-27 2008-07-23 Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07014820A EP2023041A1 (fr) 2007-07-27 2007-07-27 Brûleur à prémélange et procédé de mise en oeuvre du brûleur
PCT/EP2008/059658 WO2009016079A1 (fr) 2007-07-27 2008-07-23 Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange
EP08786350A EP2171353A1 (fr) 2007-07-27 2008-07-23 Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange

Publications (1)

Publication Number Publication Date
EP2171353A1 true EP2171353A1 (fr) 2010-04-07

Family

ID=38984079

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07014820A Withdrawn EP2023041A1 (fr) 2007-07-27 2007-07-27 Brûleur à prémélange et procédé de mise en oeuvre du brûleur
EP08786350A Withdrawn EP2171353A1 (fr) 2007-07-27 2008-07-23 Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07014820A Withdrawn EP2023041A1 (fr) 2007-07-27 2007-07-27 Brûleur à prémélange et procédé de mise en oeuvre du brûleur

Country Status (5)

Country Link
US (1) US20100183991A1 (fr)
EP (2) EP2023041A1 (fr)
JP (1) JP2010534782A (fr)
CN (1) CN101765742B (fr)
WO (1) WO2009016079A1 (fr)

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ITTO20100378A1 (it) * 2010-05-05 2011-11-06 Avio Spa Gruppo di iniezione per un combustore di una turbina a gas
EP2385307A1 (fr) * 2010-05-05 2011-11-09 AVIO S.p.A. Ensemble d'injection de chambre de combustion de turbine à gaz et procédé d'alimentation de mélange de carburant de chambre de combustion
US9091444B2 (en) 2010-05-05 2015-07-28 Avio S.P.A. Gas turbine combustor injection assembly, and combustor fuel mixture feed method

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WO2009016079A1 (fr) 2009-02-05
CN101765742A (zh) 2010-06-30
EP2023041A1 (fr) 2009-02-11
JP2010534782A (ja) 2010-11-11
CN101765742B (zh) 2012-04-25
US20100183991A1 (en) 2010-07-22

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