EP0704657B1 - Brûleur - Google Patents

Brûleur Download PDF

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Publication number
EP0704657B1
EP0704657B1 EP95810587A EP95810587A EP0704657B1 EP 0704657 B1 EP0704657 B1 EP 0704657B1 EP 95810587 A EP95810587 A EP 95810587A EP 95810587 A EP95810587 A EP 95810587A EP 0704657 B1 EP0704657 B1 EP 0704657B1
Authority
EP
European Patent Office
Prior art keywords
flow
arrangement according
burner arrangement
mixing path
swirl generator
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
EP95810587A
Other languages
German (de)
English (en)
Other versions
EP0704657A2 (fr
EP0704657A3 (fr
Inventor
Thomas Ruck
Thomas Dr. Sattelmayer
Christian Dr. Steinbach
Klaus Dr. Döbbeling
Jürgen Dr. Haumann
Hans Peter Knöpfel
Bettina Dr. Paikert
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.)
Alstom SA
Original Assignee
ABB Alstom Power Switzerland Ltd
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 Alstom Power Switzerland Ltd filed Critical ABB Alstom Power Switzerland Ltd
Publication of EP0704657A2 publication Critical patent/EP0704657A2/fr
Publication of EP0704657A3 publication Critical patent/EP0704657A3/fr
Application granted granted Critical
Publication of EP0704657B1 publication Critical patent/EP0704657B1/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
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • F23D11/40—Mixing tubes; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately 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 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/40—Inducing local whirls around flame
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2202/00—Liquid fuel burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability

Definitions

  • the present invention relates to a burner according to the preamble of claim 1.
  • EP-A1-0 321 809 describes a shell consisting of several shells conical burner, so-called double cone burner, for Generation of a closed swirl flow in the cone head has become known, which due to the increasing swirl along the cone tip becomes unstable and into an annular swirl flow with reverse flow in the core.
  • Fuels such as gaseous fuels are produced along the the individual adjacent shells formed channels, too Called air inlet slots, injected and homogeneous with the Air mixes before combustion by ignition at the stagnation point the backflow zone or backflow bubble, which acts as a flame holder is used.
  • Liquid fuels will be preferably injected via a central nozzle on the burner head and then evaporate in the cone cavity.
  • a combustion arrangement in particular goes under Reference to the cross-sectional view according to Figure 2, a central to a supply air duct 23 arranged fuel nozzle 18 provides.
  • the one with the supply air atomized fuel is directed toward a swirl chamber 32, the one provides convex wall 26 with an axial inlet opening 42, in turn Swirl plates 44 are mounted.
  • a Hollow cylinder provided that together with the swirl chamber the combustion chamber forms.
  • the swirled fuel-air mixture becomes inside the swirl chamber 32 ignited, the ignited fuel-air mixture axially in the direction of hollow cylindrical space 31 spreads, in which a plurality of cutting blades 72 protrude downstream.
  • the blades 72 are arranged such that the axial outer areas of the developing flame in a variety of secondary spiral flame eddies are separated.
  • the US 1,778,194 describes a burner with a flow tube 6, in the Fuel is injected coaxially via a fuel nozzle, namely in opposite direction to the flow direction in the flow channel 6 combustion air introduced by means of a blower 19.
  • the flow pressure of the combustion supply air becomes that within the flow channel 6 redirected atomized fuel in its original direction of propagation and carried by the combustion air through the flow channel 6.
  • an improved mixing of the fuel-air mixture within the Flow channel 6 is a free-running propeller centered on flow channel 6 arranged, which causes a swirl downstream of the fuel-air mixture.
  • the swirled fuel-air mixture subsequently enters the combustion chamber, in which is ignited.
  • Upstream of the injection nozzle and in Helical baffles are also arranged downstream provided to prevent the flow passing through the baffles To convey the axis of propagation rotating flow movement.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies based on precautions for a burner of the type mentioned propose by which a perfect premix of fuels of various types is achieved.
  • the proposed burner has one on the head side and upstream Mixing section on a swirl generator, which is preferred can be interpreted in such a way that the aerodynamic Basic principles of the so-called double-cone burner according to EP-A1-0 321 809 can be used. Basically, however, is that Use of an axial or radial swirl generator possible.
  • the mixing section itself preferably consists of a tubular one Mixing element, hereinafter called mixing tube, which a perfect premixing of different fuelskind allowed.
  • the flow from the swirl generator is seamless into the mixing tube initiated: This happens through a transition geometry, which consists of transition channels, which in the initial phase this mixing tube are excluded, and which the flow in the subsequent effective flow cross-section transfer the mixing tube.
  • This lossless Flow initiation between swirl generator and mixing tube prevented first the immediate formation of a backflow zone at the exit of the swirl generator.
  • the swirl strength in the swirl generator is above its Geometry chosen so that the vertebra does not burst in the mixing tube, but further downstream at the combustion chamber inlet takes place, the length of this mixing tube dimensioned so is that there is sufficient mix quality for everyone Fuel types results.
  • the twist strength results from the design the corresponding cone angle, the air inlet slots and their number.
  • the axial speed profile has a pronounced profile in the mixing tube Maximum on the axis and thereby prevents backfire in this area.
  • the axial speed drops down to the wall.
  • various measures are provided: For example, on the one hand, the entire speed level by using a mixing tube with a sufficient Lift small diameter.
  • Another possibility consists of only the outside speed of the Increase mixing tube by a small part of the combustion air over an annular gap or through filming holes flows into the mixing tube downstream of the transition channels.
  • Part of the pressure loss that may be generated can be caused by Attachment of a diffuser at the end of the mixing tube compensated become.
  • the combustion chamber closes at the end of the mixing tube a cross-sectional leap.
  • a central one is formed here Backflow zone, the properties of which are those of a flame holder are.
  • transition channels to initiate the flow affects from the swirl generator in the mixing tube, so to say that the course of these transition channels is spiral narrowing or expanding, according to the effective subsequent flow cross-section of the mixing tube.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator 100 effective, the design of which in the following Fig. 2-5 shown and described in more detail becomes.
  • This swirl generator 100 is a conical one Formations that are tangential multiple times from a tangential inflowing combustion air flow 115 is applied becomes.
  • the flow that forms here is based on a transition geometry provided downstream of the swirl generator 100 transitioned seamlessly into a transition piece 200, in such a way that no separation areas can occur there.
  • the configuration of this transition geometry is under Fig. 6 described in more detail.
  • This transition piece 200 is on the outflow side the transition geometry through a tube 20 lengthened, both parts of the actual mixing tube 220 of the burner.
  • the mixing tube 220 consist of a single piece, i.e. then that the Transition piece 200 and tube 20 into a single contiguous Formations are fused, the characteristics of each part are preserved.
  • a transition piece 200 and tube 20 created from two parts so these are connected by a bushing ring 10, the same bushing ring 10 on the head side as anchoring surface for the swirl generator 100 serves.
  • Such a sleeve ring 10 has it also the advantage that different mixing tubes are used can be. Downstream of the tube 20 is located the actual combustion chamber 30, which here only by the flame tube is symbolized.
  • the mixing tube 220 met the condition that a defined downstream of the swirl generator 100 Mixing section is provided in which a perfect Premixing of fuels of various types achieved becomes.
  • This mixing section ie the mixing tube 220, enables furthermore a loss-free flow guidance, so that also in operative connection with the transition geometry initially cannot form a backflow zone, which means over the length of the Mixing tube 220 to the quality of the mixture for all types of fuel Influence can be exercised.
  • This mixing tube 220 has but another property, which is that in the mixing tube 220 itself the axial speed profile pronounced maximum on the axis, so that a Back ignition of the flame from the combustion chamber is not possible. However, it is correct that with such a configuration this axial velocity drops towards the wall.
  • a diffuser not shown in the figure, is provided becomes.
  • a combustion chamber closes at the end of the mixing tube 220 30 on, between the two flow cross-sections a cross-sectional jump is present. Only here forms a central backflow zone 50, which has the properties a flame holder.
  • FIG. 2 In order to better understand the structure of the swirl generator 100 it is advantageous if, at the same time as FIG. 2, at least FIG. 3 is used. Furthermore, this Fig. 2 is not unnecessary to be confusing, they are those according to the Figure 3 schematically shown guide plates 121a, 121b only hinted been recorded. In the following, the Description of Fig. 2 as required on the figures mentioned pointed out.
  • the first part of the burner according to FIG. 1 forms the one according to FIG. 2 shown swirl generator 100.
  • This consists of two hollow conical partial bodies 101, 102 which are offset from one another are nested.
  • the number of conical Partial body can of course be larger than two, such as Figures 4 and 5 show; this depends on how each further will be explained in more detail below, depending on the type of debt collection of the whole burner. It is with certain operating constellations not excluded one from one single spiral existing swirl generator.
  • the Offset of the respective central axis or longitudinal symmetry axes 201b, 202b of the tapered partial bodies 101, 102 to one another creates a mirror image of the neighboring wall Arrangement, each a tangential channel, i.e.
  • the cone shape of the one shown Partial body 101, 102 has a flow direction certain fixed angle. Of course, depending on the operational use, can the partial body 101, 102 in the direction of flow have an increasing or decreasing taper similar to a trumpet or Tulip. The latter two Shapes are not included in the drawing as they are for the expert can be easily understood.
  • the two tapered partial bodies 101, 102 each have a cylindrical Initial part 101a, 102a, which also, analogous to the tapered Partial bodies 101, 102, offset from one another, so that the tangential air inlet slots 119, 120 via the entire length of the swirl generator 100 are present.
  • a nozzle 103 is preferred for a liquid fuel 112, the injection of which 104 with the narrowest cross section of the through conical partial body 101, 102 formed conical cavity 114 coincides.
  • the injection capacity and the type of this Nozzle 103 depends on the specified parameters of the respective burner.
  • the swirl generator can 100 purely conical, i.e. without cylindrical starting parts 101a, 102a.
  • the tapered body 101, 102 also each have a fuel line 108, 109 on which along the tangential air inlet slots 119, 120 arranged and provided with injection openings 117 are, by which preferably a gaseous fuel 113 injected into the combustion air 115 flowing through there is how the arrows 116 symbolize this.
  • This Fuel lines 108, 109 are preferably at the latest End of tangential inflow, before entering the cone cavity 114, placed, this for an optimal Obtain air / fuel mixture.
  • fuel introduced 112 normally a liquid fuel, whereby a mixture formation with another medium without any problems is possible. This fuel 112 will tip under one Angle injected into the cone cavity 114.
  • the construction of the swirl generator 100 is also excellent, the size to change the tangential air inlet slots 119, 120, with which without changing the overall length of the swirl generator 100 a relatively wide range of operations can be covered can.
  • the partial bodies 101, 102 are also in another level slidable to each other, which even an overlap of the same can be provided. It is further possible, the partial body 101, 102 by an opposite to interleave rotating movement in a spiral. So it is possible to change the shape, size and the configuration of the tangential air inlet slots 119, 120 to vary arbitrarily, with which the swirl generator 100 without Changing its overall length is universally applicable.
  • FIG Baffles 121a, 121b The geometric configuration of FIG Baffles 121a, 121b. They have a flow initiation function these, according to their length, the respective End of the tapered partial body 101, 102 in the direction of flow extend towards the combustion air 115.
  • the Channeling the combustion air 115 into the cone cavity 114 can by opening or closing the guide plates 121a, 121b by one in the area of the entry of this channel into the Cone cavity 114 placed pivot point 123 can be optimized, this is particularly necessary if the original gap size of the tangential air inlet slots 119, 120 dynamic should be changed.
  • you can dynamic arrangements can also be provided statically by required guide plates with a fixed component form the tapered partial bodies 101, 102.
  • the can also Swirl generator 100 can also be operated without baffles, or other aids can be provided for this.
  • FIG. 4 shows that the swirl generator 100 now made up of four partial bodies 130, 131, 132, 133 is.
  • the associated longitudinal symmetry axes for each partial body are marked with the letter a.
  • This configuration can be said that because of the generated lower twist strength and in cooperation with one suitably suitably enlarged slot width, the bursting of the vortex flow on the downstream side of the To prevent swirl in the mixing tube, making the mixing tube can best fulfill the role intended for him.
  • Fig. 5 differs from Fig. 4 in so far as here the partial bodies 140, 141, 142, 143 have a blade profile shape, which is intended to provide a certain flow becomes. Otherwise, the mode of operation of the swirl generator stayed the same.
  • the admixture of fuel 116 in the combustion air flow 115 happens from the inside the blade profiles out, i.e. the fuel line 108 is now integrated in the individual blades. Also here are the longitudinal axes of symmetry to the individual partial bodies marked with the letter a.
  • the transition geometry is for a swirl generator 100 with four partial bodies, corresponding to FIG. 4 or 5, built up. Accordingly, the transition geometry points as natural extension of the upstream parts four transition channels 201 on, making up the cone quarter area the partial body mentioned is extended until it hits the wall of the tube 20 respectively. of the mixing tube 220 cuts.
  • the same considerations also apply when the swirl generator from a principle other than that described in FIG. 2, is constructed.
  • the one running downward in the direction of flow The area of the individual transition channels 201 has a in the direction of flow in a spiral shape, which describes a crescent shape, corresponding to the The fact that the flow cross section of the Transition piece 200 flared in the direction of flow.
  • the swirl angle of the transition channels 201 in the flow direction is selected so that the pipe flow then up to A cross-sectional jump at the combustion chamber inlet is still sufficient large distance remains to make a perfect premix with to manage the injected fuel. Further increases the axial speed is also affected by the above-mentioned measures on the mixing tube wall downstream of the swirl generator.
  • the transition geometry and the measures in the area of the mixing tube cause a significant increase in the axial speed profile towards the center of the mixing tube, so that the danger of early ignition is decisively counteracted becomes.

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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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Air Supply (AREA)

Claims (14)

  1. Arrangement de brûleur pour un générateur calorifique, qui est composé essentiellement d'un générateur de tourbillon (100) pour un courant d'air de combustion et des moyens (103) à injecter de combustible, ainsi que d'un trajet de mélange, disposé en aval dudit générateur de tourbillon (100),
    caractérisé en ce que ledit trajet de mélange (220) comprend des conduits de transition (201), qui s'étendent à l'intérieur d'une première partie dudit trajet (200) en sens d'écoulement afin de passer un courant (40), formé dans ledit générateur de tourbillon (100), dans la partie de passage d'écoulement (20) dudit trajet de mélange (220), qui suit en aval desdits conduits de transition (201).
  2. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que ledit trajet de mélange (220) est configuré de sous forme d'un élément de mélange tubulaire.
  3. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que le nombre desdits conduits de transition (201) dans ledit trajet de mélange (220) correspond au nombre desdits segments de corps dudit générateur de tourbillon (100).
  4. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que ledit trajet de mélange (220) est muni des orifices en tant que des alésages à former une nappe (21) pour l'injection d'un courant d'air en aval desdits conduits de transition (201) en sens d'écoulement et en direction périphérique.
  5. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que ledit trajet de mélange (220) est muni des orifices tangentielles pour l'injection d'un courant d'air en aval desdits conduits de transition (201).
  6. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que la section de passage d'écoulement (20) dudit trajet de mélange (220) en aval desdits conduits de transition (201) est plus petite que, égale à ou plus large que la section de passage du courant (40) formé dans ledit générateur de tourbillon (100).
  7. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que lesdits conduits de transition (201) recouvrent l'extrémité frontale dudit trajet de mélange (220) en secteurs, en s'étendant sous forme d'un tourbillon en sens d'écoulement.
  8. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce qu'un diffuseur est disposé à l'extrémité dudit trajet de mélange (220).
  9. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce qu'une chambre de combustion (30) est disposée en aval dudit trajet de mélange (220), en ce qu'une discontinuité en section transversale est formée entre ledit trajet de mélange (220) et ladite chambre de combustion (30), qui marque la section de passage initiale d'écoulement de ladite chambre de combustion (30), et en ce qu'il est possible d'achever une zone de débit inverse (50) dans la zone de cette discontinuité en section transversale.
  10. Arrangement de brûleur selon la revendication 1,
    caractérisé en ce que ledit générateur de tourbillon (100) est composé d'au moins deux segments de corps coniques creux (101, 102; 130, 131, 132, 133; 140, 141, 142, 143), qui sont imbriqués l'un dans l'autre en sens d'écoulement, en ce que les axes de symétrie longitudinaux respectifs (101b, 102b; 130a, 131a, 132a, 133a; 140a, 141a, 142a, 143a) desdits segments de corps s'étendent à un déport l'un relatif à l'autre de façon, que les parois adjacentes desdits segments de corps forment des conduits tangentiels (119, 120) pour un courant d'air de combustion (115) le long de leur étendue, et en ce qu'au moins un injecteur de combustible (103) est disposé dans la cavité du cône (114) formé par lesdits segments de corps.
  11. Arrangement de brûleur selon la revendication 10,
    caractérisé en ce que des injecteurs de combustible (117) supplémentaires sont disposés dans la zone desdits conduits tangentiels (119, 120) le long de leur étendue en sens longitudinal.
  12. Arrangement de brûleur selon la revendication 10,
    caractérisé en ce que lesdits segments de corps (140, 141, 142, 143) présentent un profil en travers à profil sous forme d'aube.
  13. Arrangement de brûleur selon la revendication 10,
    caractérisé en ce que lesdits segments de corps présentent un angle de cône invariable ou une inclinaison du cône, qui s'augmente ou décroít.
  14. Arrangement de brûleur selon la revendication 10,
    caractérisé en ce que lesdits segments de corps sont imbriqués l'un dans l'autre sous forme hélicoïdale.
EP95810587A 1994-10-01 1995-09-20 Brûleur Expired - Lifetime EP0704657B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4435266A DE4435266A1 (de) 1994-10-01 1994-10-01 Brenner
DE4435266 1994-10-01

Publications (3)

Publication Number Publication Date
EP0704657A2 EP0704657A2 (fr) 1996-04-03
EP0704657A3 EP0704657A3 (fr) 1997-07-30
EP0704657B1 true EP0704657B1 (fr) 2001-11-07

Family

ID=6529801

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810587A Expired - Lifetime EP0704657B1 (fr) 1994-10-01 1995-09-20 Brûleur

Country Status (8)

Country Link
US (1) US5588826A (fr)
EP (1) EP0704657B1 (fr)
JP (1) JP3649785B2 (fr)
KR (1) KR960014753A (fr)
CN (1) CN1090728C (fr)
AT (1) ATE208480T1 (fr)
CA (1) CA2154941A1 (fr)
DE (2) DE4435266A1 (fr)

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WO2006048405A1 (fr) * 2004-11-03 2006-05-11 Alstom Technology Ltd Bruleur a premelange
EP2071156A1 (fr) 2007-12-10 2009-06-17 ALSTOM Technology Ltd Système de distribution de carburant d'une turbine à gaz avec ensemble brûleur à plusieurs étages
EP3062019A1 (fr) 2015-02-27 2016-08-31 General Electric Technology GmbH Procédé et dispositif de stabilisation de flamme dans un brûleur d'un moteur à combustion stationnaire

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DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19547913A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19549143A1 (de) * 1995-12-29 1997-07-03 Abb Research Ltd Gasturbinenringbrennkammer
KR100381719B1 (ko) * 1995-12-29 2003-08-14 고려화학 주식회사 수용성 방청도료 조성물
DE19610930A1 (de) * 1996-03-20 1997-09-25 Abb Research Ltd Brenner für einen Wärmeerzeuger
US5954496A (en) * 1996-09-25 1999-09-21 Abb Research Ltd. Burner for operating a combustion chamber
DE19639301A1 (de) 1996-09-25 1998-03-26 Abb Research Ltd Brenner zum Betrieb einer Brennkammer
DE19640198A1 (de) * 1996-09-30 1998-04-02 Abb Research Ltd Vormischbrenner
DE19649486A1 (de) * 1996-11-29 1998-06-04 Abb Research Ltd Brennkammer
DE19654009B4 (de) * 1996-12-21 2006-05-18 Alstom Vormischbrenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff
DE19654116A1 (de) 1996-12-23 1998-06-25 Abb Research Ltd Brenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff
KR100461575B1 (ko) * 1996-12-30 2005-06-27 고려화학 주식회사 아크릴에멀젼수지를이용한수계방청도료조성물
DE59710046D1 (de) 1997-03-20 2003-06-12 Alstom Switzerland Ltd Gasturbine mit toroidaler Brennkammer
DE19720786A1 (de) * 1997-05-17 1998-11-19 Abb Research Ltd Brennkammer
DE59708564D1 (de) * 1997-07-15 2002-11-28 Alstom Verfahren und Vorrichtung zum Minimieren thermoakustischer Schwingungen in Gasturbinenbrennkammern
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE59709510D1 (de) 1997-09-15 2003-04-17 Alstom Switzerland Ltd Kombinierte Druckzerstäuberdüse
EP0903540B1 (fr) * 1997-09-19 2003-04-09 ALSTOM (Switzerland) Ltd Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE59709446D1 (de) * 1997-10-31 2003-04-10 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
EP0918190A1 (fr) * 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE59709868D1 (de) * 1997-12-22 2003-05-22 Alstom Switzerland Ltd Zweistufige Druckzerstäuberdüse
DE59709924D1 (de) 1997-12-22 2003-05-28 Alstom Switzerland Ltd Zweistufige Druckzerstäuberdüse
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
DE19912701B4 (de) * 1999-03-20 2006-01-19 Alstom Brennkammerwand
DE10049205A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners
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CA2154941A1 (fr) 1996-04-02
DE59509802D1 (de) 2001-12-13
CN1090728C (zh) 2002-09-11
EP0704657A2 (fr) 1996-04-03
JPH08114307A (ja) 1996-05-07
US5588826A (en) 1996-12-31
CN1131737A (zh) 1996-09-25
DE4435266A1 (de) 1996-04-04
KR960014753A (ko) 1996-05-22
ATE208480T1 (de) 2001-11-15
EP0704657A3 (fr) 1997-07-30
JP3649785B2 (ja) 2005-05-18

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