EP0675322B1 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

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Publication number
EP0675322B1
EP0675322B1 EP95810184A EP95810184A EP0675322B1 EP 0675322 B1 EP0675322 B1 EP 0675322B1 EP 95810184 A EP95810184 A EP 95810184A EP 95810184 A EP95810184 A EP 95810184A EP 0675322 B1 EP0675322 B1 EP 0675322B1
Authority
EP
European Patent Office
Prior art keywords
flow
duct
vortex generator
vortex
edge
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.)
Expired - Lifetime
Application number
EP95810184A
Other languages
German (de)
English (en)
Other versions
EP0675322A2 (fr
EP0675322A3 (fr
Inventor
Rolf Dr. Althaus
Jakob 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 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 EP0675322A2 publication Critical patent/EP0675322A2/fr
Publication of EP0675322A3 publication Critical patent/EP0675322A3/fr
Application granted granted Critical
Publication of EP0675322B1 publication Critical patent/EP0675322B1/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
    • F23D23/00—Assemblies of two or more burners
    • 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
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • F05B2240/122—Vortex generators, turbulators, or the like, for mixing

Definitions

  • the invention relates to a premix burner, essentially consisting of a pilot burner and several around the Pilot burners arranged around main burners.
  • the mixing of fuel into one in a premix channel flowing combustion air flow usually happens by means of radial injection of the fuel into the channel Cross jet mixers.
  • the impulse of the fuel is however so low that an almost complete mixing first after a distance of approx. 100 canal heights.
  • Venturi mixers are used.
  • premix burners can be used as flame-holding burners of the double-cone design.
  • Double cone burners are for example from EP-B1-0 321 809 are known and will be described later with reference to FIGS. 1 and 3.
  • the fuel, there natural gas, is in the entry columns in the combustion air flowing in from the compressor via a Injected row of injector nozzles. These are in the Usually evenly distributed over the entire gap.
  • the invention is therefore based on the object Premix burner of the type mentioned at the beginning of a measure create with which within the shortest distance an intimate Mixing of combustion air and fuel is achieved with at the same time even speed distribution in the mixing zone. Furthermore, with such a burner without Kickback using a mechanical flame holder the flame can be avoided with certainty.
  • the measure should also be suitable for existing premix combustion chambers retrofit.
  • This type of mixture is particularly suitable for the fuel with a relatively low form and a large dilution to mix into the combustion air.
  • a small form of the fuel is particularly important when using medium and low calorific fuel gases are an advantage.
  • the energy required for mixing becomes one essential part from the flow energy of the fluid taken from the higher volume flow, namely the combustion air.
  • the downstream arrangement of a Venturi nozzle behind the Vortex generators have the advantage of being the largest Constriction of the Venturi nozzle a simple means in has the hand to put the fuel in with the smallest back pressure to initiate the swirled flow.
  • the venturi nozzle has with the correct dimensioning, the advantage that the Flow velocity in it the flame velocity exceeds, so the flame does not enter the injection plane of fuel can kick back.
  • Draw the vortex generators upstream of the Venturi nozzle is characterized by a roof surface and two side surfaces, the side surfaces being flush with an identical duct wall are and include an arrow angle a and the longitudinal edges of the roof surface being flush with the longitudinal ones protruding into the flow channel Edges of the side surfaces and at an angle of attack e run to the canal wall.
  • the sharp connecting edge is the exit-side edge of the vortex generator and it runs perpendicular to that Channel wall, with which the side surfaces are flush, is so the non-formation of a trailing area is an advantage.
  • the connecting edge of the two side surfaces downstream edge of the vortex generator forms while consequently, the one running across the channel Edge of the roof surface that was first affected by the channel flow Edge, so there are two on a vortex generator the same but opposite vortices are generated. It is a vortex-neutral flow pattern in which the direction of rotation of the two vertebrae ascending in the area of the connecting edge is.
  • This combustion chamber can be both an annular combustion chamber or a silo combustion chamber, several such burners each on the front wall 100 are arranged.
  • a centrally Pilot burner 101 grouped around six main burners 52.
  • the pilot burner is in the example case a premix burner of the double cone type, this is not mandatory.
  • the decisive factor is that this pilot burner should have the smallest possible geometry. In it should about 10-30% of the fuel is burned.
  • the Main burners 52 are cylindrical in shape. At their tubular Wall 54 are initially vortex generators in the direction of flow 9 arranged, the outlet into a Venturi nozzle 50 flows.
  • the fuel is the pilot burner and the Main burners supplied via fuel lances 120 and 51 respectively.
  • the combustion air comes from a not shown Plenum into the interior 103 of the housing, from where they in The direction of the arrow flows into the burners 101, 52.
  • premix burner 101 is a so-called Double cone burner, as for example from EP-B1-0 321 809 is known. It essentially consists of two hollow, conical part-bodies 111, 112, which are in the direction of flow are nested. Here are the respective central axes 113, 114 of the two partial bodies offset against each other. The neighboring walls of the the two partial bodies form tangential lines in their longitudinal extent Slots 119 for the combustion air on this Way into the interior of the burner. There is a first one Fuel nozzle 116 arranged for liquid fuel. Of the Fuel is injected into the hollow cone at an acute angle injected. The resulting tapered fuel profile will enclosed by the combustion air flowing in tangentially.
  • the concentration of the fuel is in the axial direction continuously as a result of mixing with the combustion air reduced.
  • the burner is also operated with gaseous fuel.
  • gaseous fuel For this are in Area of tangential slots 119 in the walls of the longitudinally distributed gas inflow openings 117 provided.
  • the mixture formation begins in gas operation with the combustion air already in the zone of Entry slots 20. It is understood that this way Mixed operation with both types of fuel is also possible is.
  • a vortex generator consists essentially of three free flowed around triangular surfaces. This is a roof area 10 and two side surfaces 11 and 13. In their longitudinal extent these surfaces run at certain angles in Flow direction.
  • the side walls of the vortex generator which are made of rectangular ones Triangles exist with their long sides on fixed a channel wall 21, preferably gas-tight. They are oriented so that they have a bump on their narrow sides form including an arrow angle ⁇ .
  • the push is designed as a sharp connecting edge 16 and is vertical to that channel wall 21 with which the side surfaces are flush.
  • the two enclosing the arrow angle ⁇ Side surfaces 11, 13 are symmetrical in shape in FIG. 4, Size and orientation and are on both sides of an axis of symmetry 17 arranged. This axis of symmetry 17 is rectified like the channel axis.
  • the roof surface 10 is transverse to the flow Channel extending and very narrow edge 15 the same channel wall 21 as the side walls 11, 13. Its longitudinal edges 12, 14 are flush with the in longitudinal edges protruding into the flow channel of the side surfaces.
  • the roof area runs under one Angle of attack ⁇ to the duct wall 21. Your longitudinal edges 12, 14 together with the connecting edge 16 form a tip 18.
  • the vortex generator can also be used with a Be provided with the floor surface with which he in a suitable manner is attached to the channel wall 21.
  • a floor area has no connection with the mode of action of the element.
  • the vortex generator works as follows: Flow around the edges 12 and 14 becomes the main flow Pair of opposing vertebrae converted. Whirl axes lie in the axis of the main flow.
  • the swirl number and the Location of vortex breakdown will be determined by appropriate Choice of the angle of attack ⁇ and the arrow angle ⁇ . With increasing angles, the vortex strength or the swirl number becomes increases and the location of the vortex burst moves upstream down to the area of the vortex generator itself. Depending on the application, these two angles are ⁇ and ⁇ through constructive conditions and through the process given yourself. Then only the need to be adjusted Length L of the element and the height h of the connecting edge 16 (Fig. 7).
  • Vortex generator 5 is a so-called half "vortex generator" the base of a vortex generator shown in FIG. 1, at which only one of the two side surfaces of the vortex generator 9a is provided with the arrow angle ⁇ / 2. The other side surface is straight and aligned in the direction of flow. In contrast to the symmetrical vortex generator only a vortex is created on the arrowed side here. It there is therefore no vortex-neutral downstream of the vortex generator Field ahead, but the flow becomes a swirl imposed.
  • the sharp connecting edge is in FIG. 6 16 of the vortex generator 9 that position by the channel flow is applied first.
  • the element is rotated by 180 °.
  • the two opposite vortices changed their sense of rotation.
  • the vortex generators are in a channel 20 built-in.
  • Another criterion which influence can take on the ratio h / H to be selected the pressure drop that flows around the vortex generator occurs. It goes without saying that with a larger ratio h / H also the pressure loss coefficient increases.
  • FIG 9 In the example shown, four vortex generators are shown in FIG 9 at a distance over the circumference of the circular cross section distributed.
  • the above mentioned amount of Channel part which is assigned to the individual vortex generator in this case corresponds to the circle radius.
  • the vortex generators 9 are mainly for mixing two currents used.
  • the main flow in the form of Combustion air attacks the transverse ones in the direction of the arrow Leading edges 15.
  • the secondary flow in the form of a gaseous and / or liquid fuel has an essential smaller mass flow than the main flow. she is in the present case downstream of the vortex generators introduced into the main flow.
  • the fuel is here via a central Fuel lance 51 injected, the mouth of which is downstream of the vortex generators. This lance is for dimensioned about 10% of the total volume flow through the channel 20.
  • a longitudinal injection of the fuel is shown in the direction of flow. In this case the injection pulse corresponds about that of the main flow pulse. I agree a cross-jet injection could be provided as well, the fuel pulse then being about twice that the main flow must be.
  • the injected fuel is carried along by the eddies and mixed with the main flow. It follows the helical one Course of the vertebrae and becomes downstream the vertebrae evenly distributed in the chamber. This reduces the - in the radial injection of Fuel in an undisturbed flow - risk of impact jets on the opposite wall and the formation of so-called "hot spots".
  • thermoacoustic Instability By their presence alone the vortex generators act as a damping measure thermoacoustic vibrations.
  • Venturi nozzle downstream of the vortex generators 52 provided. This is dimensioned so that at an exit speed of about 80-150 m / sec Flow velocity in the narrowest cross section about 150-180 m / sec. The distance of the narrowest cross section to the Trailing edges 16 of the vortex generators will be chosen so that the generated vortex in the narrowest cross section are already fully trained. The location of the fuel injection is at the level of the largest constriction the Venturi nozzle.
  • Figures 8 and 9 show a top view of an embodiment variant of the vortex generator and in a front view its arrangement in a circular channel.
  • the two the side surfaces 11 and 13 have a different length.
  • the width of the Vortex generator then of course a different one Angle of attack ⁇ on.
  • Such a variant has Effect that creates vortices of different strength become.
  • through the different vertebrae will be the originally swirl-free Main flow downstream of the vortex generators Swirl forced, as indicated in Fig. 9.
  • a such configuration works well as a standalone, compact burner unit. When using multiple such units, for example in a gas turbine ring combustor, can the swirl imposed on the main flow can be exploited to determine the cross-ignition behavior of the burner configuration, e.g. at partial load.
  • the invention is not limited to that described and examples shown.
  • the Arrangement of the vortex generators in the network are many combinations possible without leaving the scope of the invention.
  • the introduction of the secondary flow into the main flow can be done in a variety of ways for example only or additionally via wall holes in the Venturi tube

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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)
  • Spray-Type Burners (AREA)

Claims (9)

  1. Brûleur à prémélange, se composant essentiellement d'un brûleur pilote (101) et de plusieurs brûleurs principaux (52) disposés autour du brûleur pilote (101),
       caractérisé en ce que
    dans les brûleurs principaux (52) présentant un canal circulaire (20), un combustible gazeux et/ou liquide est injecté en un écoulement secondaire dans un écoulement principal gazeux,
    l'écoulement principal est d'abord conduit sur des générateurs de tourbillons (9), dont plusieurs sont disposés l'un à côté de l'autre sur la périphérie du canal parcouru (20),
    une tuyère de Venturi (50) est disposée en aval des générateurs de tourbillons (9),
    et l'écoulement secondaire est introduit dans le canal (20) dans la région du plus grand étranglement de la tuyère de Venturi (50).
  2. Brûleur à prémélange suivant la revendication 1, caractérisé en ce que le brûleur pilote (101) fonctionne suivant le principe du double cône, avec essentiellement deux corps partiels (111, 112) coniques creux, imbriqués l'un dans l'autre dans la direction de l'écoulement, dont les axes centraux respectifs (113, 114) sont déportés l'un par rapport à l'autre, les parois voisines des deux corps partiels (111, 112) formant, suivant leur dimension longitudinale, des fentes tangentielles (119) pour l'air de combustion, et des ouvertures d'entrée de gaz (117) réparties en direction longitudinale étant prévues dans les parois des deux corps partiels, dans la région des fentes tangentielles (119).
  3. Brûleur à prémélange suivant la revendication 1, caractérisé en ce que
    un générateur de tourbillons (9) présente trois faces librement balayées, qui s'étendent dans la direction de l'écoulement et dont l'une forme la face de toit (10) et les deux autres les faces latérales (11, 13),
    les faces latérales (11, 13) sont jointives à un même segment de paroi (21) du canal et forment l'une avec l'autre un angle de flèche (α),
    la face de toit (10) s'applique, par une arête (15) orientée transversalement au canal parcouru (20), sur le même segment de paroi (21) que les parois latérales,
    et les arêtes (12, 14) orientées longitudinalement de la face de toit, qui sont jointives aux arêtes orientées longitudinalement, et pénétrant dans le canal d'écoulement, des faces latérales sont orientées vers le segment de paroi (21) sous un angle d'incidence .
  4. Brûleur à prémélange suivant la revendication 3, caractérisé en ce que les deux faces latérales (11, 13) du générateur de tourbillons (9), qui forment l'angle de flèche (α), sont disposées symétriquement par rapport à un axe de symétrie (17).
  5. Brûleur à prémélange suivant la revendication 3, caractérisé en ce que les deux faces latérales (11, 13) formant l'angle de flèche (α) comprennent une arête (16) de liaison l'une à l'autre, qui forme une pointe (18) en conjonction avec les arêtes orientées longitudinalement (12, 14) de la face de toit (10), et en ce que l'arête de liaison se trouve en position radiale par rapport au canal circulaire (20).
  6. Brûleur à prémélange suivant la revendication 5, caractérisé en ce que l'arête de liaison (16) et/ou les arêtes orientées longitudinalement (12, 14) de la face de toit (10) sont au moins approximativement des arêtes vives.
  7. Brûleur à prémélange suivant la revendication 4, caractérisé en ce que l'axe de symétrie (17) du générateur de tourbillons (9) est orienté parallèlement à l'axe du canal, l'arête de liaison (16) des deux faces latérales (11, 13) formant l'arête aval du générateur de tourbillons (9), et l'arête (15) de la face de toit (10) orientée transversalement au canal parcouru (20) constituant l'arête atteinte en premier par l'écoulement principal.
  8. Brûleur à prémélange suivant la revendication 1, caractérisé en ce que le rapport entre la hauteur (h) du générateur de tourbillons et la hauteur (H) du canal est choisi de telle façon que le tourbillon obtenu remplisse, immédiatement en aval du générateur de tourbillons (9), la pleine hauteur du canal ou la pleine hauteur de la partie de canal associée au générateur de tourbillons.
  9. Brûleur à prémélange suivant la revendication 1, caractérisé en ce que l'écoulement secondaire est introduit au moyen d'une injection longitudinale ou d'une injection à jet transversal, par une lance à combustible (51) disposée en position centrale dans le canal (20).
EP95810184A 1994-04-02 1995-03-17 Brûleur à prémélange Expired - Lifetime EP0675322B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4411622A DE4411622A1 (de) 1994-04-02 1994-04-02 Vormischbrenner
DE4411622 1994-04-02

Publications (3)

Publication Number Publication Date
EP0675322A2 EP0675322A2 (fr) 1995-10-04
EP0675322A3 EP0675322A3 (fr) 1996-05-15
EP0675322B1 true EP0675322B1 (fr) 1999-04-28

Family

ID=6514606

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810184A Expired - Lifetime EP0675322B1 (fr) 1994-04-02 1995-03-17 Brûleur à prémélange

Country Status (5)

Country Link
US (1) US5558515A (fr)
EP (1) EP0675322B1 (fr)
JP (1) JPH07280224A (fr)
CN (1) CN1118858A (fr)
DE (2) DE4411622A1 (fr)

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US20150159878A1 (en) * 2013-12-11 2015-06-11 Kai-Uwe Schildmacher Combustion system for a gas turbine engine
JP6177187B2 (ja) * 2014-04-30 2017-08-09 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器、ガスタービン、制御装置及び制御方法
EP3081862B1 (fr) * 2015-04-13 2020-08-19 Ansaldo Energia Switzerland AG Agencement de génération de vortex pour un brûleur à pré-mélange d'une turbine à gaz et turbine à gaz avec un tel agencement de génération de vortex
CN104896511B (zh) * 2015-05-29 2017-03-22 北京航空航天大学 一种用于低排放燃烧室的燃油预混装置
CN105240847A (zh) * 2015-11-19 2016-01-13 哈尔滨东安发动机（集团）有限公司 一种燃烧室防回火结构
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CN113405093A (zh) * 2021-05-06 2021-09-17 中国科学院工程热物理研究所 燃料喷口、燃烧装置及燃烧控制方法
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Also Published As

Publication number Publication date
CN1118858A (zh) 1996-03-20
JPH07280224A (ja) 1995-10-27
DE59505747D1 (de) 1999-06-02
US5558515A (en) 1996-09-24
EP0675322A2 (fr) 1995-10-04
EP0675322A3 (fr) 1996-05-15
DE4411622A1 (de) 1995-10-05

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