EP0718561B1 - Brennkammer - Google Patents

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Publication number
EP0718561B1
EP0718561B1 EP95810763A EP95810763A EP0718561B1 EP 0718561 B1 EP0718561 B1 EP 0718561B1 EP 95810763 A EP95810763 A EP 95810763A EP 95810763 A EP95810763 A EP 95810763A EP 0718561 B1 EP0718561 B1 EP 0718561B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
flow
fuel
stage
combustion
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
EP95810763A
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German (de)
English (en)
French (fr)
Other versions
EP0718561A2 (de
EP0718561A3 (de
Inventor
Rolf Dr. Althaus
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 Schweiz AG
Original Assignee
ABB Schweiz 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 ABB Schweiz AG filed Critical ABB Schweiz AG
Publication of EP0718561A2 publication Critical patent/EP0718561A2/de
Publication of EP0718561A3 publication Critical patent/EP0718561A3/de
Application granted granted Critical
Publication of EP0718561B1 publication Critical patent/EP0718561B1/de
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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • F23C6/047—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure with fuel supply in stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the present invention relates to a combustion chamber according to Claim 1. It also concerns a procedure to operate such a combustion chamber.
  • EP-A-0 694 740 discloses a two-stage combustion chamber in which in a first stage a fuel / air mixture is burned by means of a catalytic converter. In the hot gases formed in this way, fuel is generated downstream of vortex generators and air was injected and burned in a second combustion chamber stage.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies the basis for a combustion chamber and a method of the beginning mentioned type, all occurring during the combustion Minimize pollutant emissions regardless which type of fuel is used.
  • the main advantage of the combustion chamber according to the invention is that there are two burner characteristics to one inventive combinations are focused, with the final purpose, especially the NOx emissions towards zero to strive.
  • the first part of the combustion chamber based on a premix combustion, only with part of the Combustion air flows through, and supplies the hot gas for the downstream second part of the combustion chamber.
  • the second Part of the combustion chamber becomes the total mass flow flows through.
  • the goal is the first part of the combustion chamber operate with the lowest possible temperature in "premix mode", the lowest possible basic NOx level of a few to achieve vppm. This is achieved by the temperature the combustion air before the first partial combustion chamber preheated to a temperature on the order of 500-700 ° C becomes.
  • This combustion air can be relatively simple the compressor end temperature has been raised to the desired level be, preferably with the fact that they are previously direct used as cooling air for the combustion chamber itself or on integrated Heat exchanger elements is passed.
  • the Hot gases are then downstream of the first partial combustion chamber by injecting the rest, in combustion air not used in the first partial combustion chamber brought to that temperature which in the second Combustion chamber part comes to self-ignition, this one second combustion chamber part is equipped with vortex generators.
  • Another advantage of the invention is that the second combustion chamber part as a single-stage load combustion chamber driven, in contrast to the first combustion chamber part, the is operated as an idle combustion chamber.
  • the second part of the combustion chamber works up to gas temperatures of approx. 1600 ° C due to the extremely good mixture is NOX neutral and delivers Total NOx potential with a very flat temperature / NOx characteristic from 1-2 vppm.
  • Another advantage of the invention is that by adjusting the temperature at the entrance to the second Combustion chamber part the ignition delay times for different fuels can be optimally adjusted.
  • FIG. 1 shows, as can be seen from the shaft axis 16, a Annular combustion chamber, which is essentially the shape of a coherent has annular or quasi-annular cylinder.
  • a combustion chamber can also be used a number of axially, quasi-axially or helically arranged and individually in self-contained combustion chambers consist.
  • the combustion chamber can also consist of a single one Pipe exist.
  • the annular combustion chamber according to FIG. 1 exists from a first 1 and a second stage 2, which one after the other are switched, and wherein the second stage 2 also actual combustion zone 11 includes.
  • the first stage 1 initially consists of a number of in the flow direction circumferentially arranged burners 100, this Brenner is further described below.
  • the NOx emissions are very low, in the order of 1-3 vppm.
  • the hot gases 4 flow into an inflow zone 5 and there they are accelerated to approx. 80-120 m / s.
  • the Inflow zone 5 is on the inside and in the circumferential direction of the channel wall 6 with a series of vortex generating elements 200, hereinafter referred to as vortex generators only, which will be discussed in more detail below.
  • the hot gases 4 are in this area by wall cooling effects and by injecting the remaining air 17, preferably by effusion cooling, this injection preferably is also carried out via the vortex generators 200, brought to a temperature of 800-1100 ° C.
  • the total air is then swirled by the vortex generators 200 in such a way that in the subsequent premixing section 7 there are no recirculation areas more in the wake of the vortex generators mentioned 200 occur.
  • the premix section 7 the can be designed as a venturi channel, several fuel lances 8 scheduled, which is the supply of a fuel 9 and a supporting air 10 take over.
  • the feeder this media to the individual fuel lances 8 can, for example made via a ring line, not shown be, the fuel supply also via the vortex generators 200 integrated fuel lances 3 made can be.
  • the one triggered by the vortex generators 200 Swirl flow ensures a large distribution of the introduced fuel 9, possibly also the admixed Support air 10 to a fuel / air mixture 19. Des the swirl flow also ensures homogenization of the Mixture of combustion air and fuel.
  • the one through the Fuel lance 8 fuel 9 injected into the hot gases 4 triggers a self-ignition, as far as these hot gases 4 those have specific temperature, which is the fuel-dependent Auto ignition can trigger.
  • the large-scale distribution of the fuel 9 continues to be guaranteed, because the peripheral component of that of the vortex generators 200 originating swirl flow is not affected. Closes behind the relatively short premixing zone 7 the combustion zone 11. The transition between the a radial cross-sectional jump 12 formed, which is initially the flow cross section of the combustion zone 11 indexed. In the area of the cross-sectional jump 12 is also a flame front 21. To reignite to avoid the flame inside the premix zone 7 the flame front 21 must be kept stable. To this For this purpose, the vortex generators 200 are designed such that in the premix zone 7 is not yet being recirculated; first after the sudden widening of the cross-section the bursting takes place the swirl flow takes place.
  • the swirl flow supports the quick reinstallation of the current behind the Cross-sectional jump 12, so that the most complete Utilization of the volume of the combustion zone 11 a high Burnout can be achieved with a short overall length.
  • this cross-sectional jump 12 forms during the Operation a flow boundary zone, in which by the negative pressure of the vortex prevailing there, which then stabilize the flame front 21 to lead.
  • These corner vortices 20 also form the ignition zones within the second stage 2.
  • the provided in the combustion zone 11 hot working gases 13 are then applied a downstream turbine 14.
  • the exhaust gases This turbine can then be used to operate a steam cycle are used, in the latter case the circuit is then a combination system.
  • the proposed method also behaves very well regarding a wide load range. Because the mix kept largely constant in the first stage 1 UHC or CO emissions can also be prevented become.
  • the constant temperature at the entrance to the second Level 2 ensures a safe auto-ignition of the mixture, regardless of the amount of fuel in the second stage 2.
  • the inlet temperature is still high enough to get you sufficient burnout in the second stage 2 even at low To reach the amount of fuel.
  • the power regulation over the gas turbine load is essentially due to the adaptation the amount of fuel in the second stage 2.
  • the first stage 1 is operated as an idle combustion chamber second stage 2 operated as a single-stage load combustion chamber.
  • FIG. 2 Cuts according to Figures 3-5 are those shown schematically in FIGS. 3-5.
  • Baffles 121a, 121b have only been hinted at. The following is the description of FIG. 2 as needed referred to the remaining figures 3-5.
  • the burner 100 of FIG. 2 consists of two hollow conical ones Partial bodies 101, 102 that are nested offset from one another are.
  • the offset of the respective central axis or longitudinal symmetry axis 201b, 202b of the tapered partial body 101, 102 creates each other on both sides, in mirror image arrangement, each with a tangential air inlet slot 119, 120 free (Fig. 3-5), through which the Combustion air 115 in the interior of burner 100, i.e. in the cone cavity 114 flows.
  • the cone shape of the one shown Partial body 101, 102 has a certain direction of flow 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 a trumpet resp.
  • 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 over the entire length of burner 100 are present.
  • a nozzle 103 is housed, its injection 104 roughly with the narrowest cross section of the through the tapered Part body 101, 102 formed conical cavity 114 coincides.
  • the injection capacity and the type of this nozzle 103 depends on the given parameters of the respective Brenner 100.
  • the burner 100 can be pure conical, that is, without cylindrical starting parts 101a, 102a his.
  • the tapered body 101, 102 have the further each have a fuel line 108, 109 which runs along the tangential entry slots 119, 120 and are provided with injection openings 117 through which preferably a gaseous fuel 113 in there combustion air 115 flowing through is injected, like this want to symbolize the arrows 116.
  • These fuel lines 108, 109 are preferably at the latest at the end of the tangential Inflow, before entering the cone cavity 114, placed in order to achieve an optimal air / fuel mixture receive.
  • the exit opening goes in the area of the inflow zone 5 of the burner 100 into a front wall 110, in which there are a number of bores 110a.
  • the latter come into operation when necessary, and ensure that dilution air or cooling air 110b the front part of the inflow zone 5 is supplied.
  • the one brought up through the nozzle 103 It is preferably a fuel liquid fuel 112, which at most with a recirculated Exhaust gas can be enriched.
  • This fuel 112 is injected into the cone cavity 114 at an acute angle.
  • a nozzle is thus formed from the nozzle 103
  • Fuel profile 105 that flows in from the tangential rotating combustion air 115 is enclosed. In axial Direction, the concentration of the fuel 112 becomes continuous through the incoming combustion air 115 to a optimal mixture degraded.
  • the burner 100 with a operated gaseous fuel 113 this can also over the fuel nozzle 103 happen, but preferably happens this via opening nozzles 117, the formation of this fuel / air mixture right at the end of the air inlet slots 119, 120 comes about.
  • the combustion air 115 is additional preheated or enriched with a recirculated exhaust gas, this supports the evaporation of the liquid fuel 112 sustainable.
  • the same considerations also apply if via the lines 108, 109 instead of gaseous liquid Fuels are supplied.
  • the tapered Partial body 101, 102 When designing the tapered Partial body 101, 102 with respect to the cone angle and Width of the tangential air inlet slots 119, 120 are to adhere to narrow limits, so that the desired Flow field of combustion air 115 at the burner outlet 100 can set.
  • the critical swirl number arises at the exit of burner 100: A also forms there Backflow zone (vortex breakdown) with a flame stabilizing Effect. Generally speaking, that is a minimization the cross section of the tangential air inlet slots 119, 120 is predestined, a backflow zone 106 to build.
  • the construction of the burner 100 is suitable another excellent, the size of the tangential air inlet slots 119, 120 change, with what no change the overall length of the burner 100 is a relatively large operational one Bandwidth can be captured.
  • the partial bodies 101, 102 also in a different plane to one another slidable, thereby even overlapping them can be controlled. It is even possible to use the partial body 101, 102 by counter-rotating motion
  • the Baffles 121a, 121b 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 the tangential air inlet slots 119, 120 motives mentioned above is to be changed.
  • these dynamic arrangements can also be provided statically become an integral part by making required baffles form with the tapered partial bodies 101, 102.
  • the burner 100 can also be operated without baffles, or other aids can be provided for this.
  • a vortex generator 200, 201, 202 essentially consists of three freely flowing triangular surfaces. These are a roof surface 210 and two side surfaces 211 and 213. In their longitudinal extension, these surfaces run at certain angles in the direction of flow.
  • the side walls of the vortex generators 200, 201, 202, which preferably consist of right-angled triangles, are fixed with their long sides on the channel wall 6 already mentioned, preferably gas-tight. They are oriented so that they form a joint on their narrow sides, including an arrow angle ⁇ .
  • the joint is designed as a sharp connecting edge 216 and is perpendicular to each channel wall 6 with which the side surfaces are flush.
  • the two side surfaces 211, 213 including the arrow angle a are symmetrical in shape, size and orientation in FIG. 4, they are arranged on both sides of an axis of symmetry 217 which is aligned in the same direction as the channel axis.
  • the roof surface 210 lies against the same channel wall 6 as the side surfaces 211, 213 with a very narrow edge 215 running transverse to the flow channel. Its longitudinal edges 212, 214 are flush with the longitudinal edges of the side surfaces 211 protruding into the flow channel , 213.
  • the roof surface 210 extends at an angle of attack e to the channel wall 6, the longitudinal edges 212, 214 of which, together with the connecting edge 216, form a point 218.
  • the vortex generator 200, 201, 202 can also be provided with a bottom surface with which it is attached to the channel wall 6 in a suitable manner. Such a floor area is, however, unrelated to the mode of operation of the element.
  • the mode of operation of the vortex generator 200, 201, 202 is the following: When flowing around edges 212 and 214, the Main flow converted into a pair of counter-rotating vortices, as schematically sketched in the figures.
  • the Vortex axes lie in the axis of the main flow.
  • the vortex strength or the number of twists increases, and the location of the vortex burst shifts upstream into the area of the vortex generator 200, 201, 202 themselves.
  • these are both angles ⁇ and ⁇ due to structural conditions and determined by the process itself. Need to be adjusted these vortex generators only in terms of length and height, as this will be explained in more detail below under FIG. 9 will arrive.
  • Fig. 7 is a so-called half "vortex generator" the base of a vortex generator shown in FIG. 6.
  • Vortex generator 201 shown here is only one of the two Provide side surfaces with the arrow angle ⁇ / 2.
  • the other Side surface is straight and aligned in the direction of flow.
  • a vortex on the swept side is created here, like this is symbolized in the figure. Accordingly, it is downstream this vortex generator does not have a vortex-neutral field, but instead a swirl is imposed on the current.
  • Fig. 8 differs from Fig. 6 in so far as here the sharp connecting edge 216 of the vortex generator 202 is the point which is affected first by the channel flow becomes. The element is therefore rotated by 180 °. How it can be seen from the illustration that the two have opposite directions Vortex changed their sense of rotation.
  • Fig. 9 shows the basic geometry of one in a channel 5 built-in vortex generator 200.
  • the influence on the ratio to be chosen of the two heights h / H is the pressure drop, that occurs when the vortex generator 200 flows around. It it goes without saying that with a larger ratio h / H the Pressure loss coefficient increases.
  • the vortex generators 200, 201, 202 are mainly used when it comes to two currents with each other to mix.
  • the main flow 4 attacked as hot gases in the direction of the arrow, the transverse edge 215, respectively the Connecting edge 216.
  • FIG. 1 there are four vortex generators 200 distributed at a distance over the circumference of the channel 5.
  • the vortex generators can be in Circumferential direction are also lined up so that none Spaces on the channel wall 6 are left blank.
  • Figures 10-16 show other possible forms of introduction of fuel in hot gases 4. These options can interact with each other and with a central Fuel injection, such as that shown in FIG. 1 emerges can be combined.
  • the fuel is added to channel wall bores 220, which are located downstream of the vortex generators, also injected via wall holes 221, which are immediately next to the side surfaces 211, 213 and in their Longitudinal extension in the same channel wall 6 are located on the the vortex generators are arranged.
  • the introduction of the Fuel through the wall holes 221 gives the generated Whirl an extra impulse, which is the lifespan of the vortex generator extended.
  • the fuel is fed through a slot 222 or injected via wall holes 223, both precautions immediately in front of the cross-canal extending edge 215 of the roof surface 210 and in the Longitudinal extension in the same channel wall 6 are located on the the vortex generators are arranged.
  • the geometry of the Wall bores 223 or the slot 222 is selected such that the fuel at a certain injection angle into the Main flow 4 is entered and the re-placed vortex generator as a protective film against the hot main flow 4 largely shielded by flow.
  • the secondary flow (See above) first of all via guides not shown through the channel wall 6 into the hollow interior of the vortex generators initiated. In this way, an internal cooling facility for the vortex generators created.
  • the fuel is injected via wall bores 224, which is located directly within the roof area 210 behind and along the one running across the channel Edge 215.
  • the vortex generator is cooled here more external than internal.
  • the emerging secondary flow forms a flow against the roof surface 210 against the hot main flow 4 shielding protective layer.
  • the fuel is injected via wall bores 225, which within the roof surface 210 along the line of symmetry 217 are staggered.
  • the channel walls 6 are particularly good before the hot main flow 4 protected because the fuel is initially on the outer circumference the vertebra is introduced.
  • the fuel is injected via wall bores 226, which are located in the longitudinal edges 212, 214 of the Roof area 210 are located.
  • This solution ensures a good one Cooling of the vortex generators because of the fuel on it Extremities emerge and thus the inner walls of the element fully washed.
  • the secondary flow is here directly put the resulting vortex into what to define Flow conditions leads.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Incineration Of Waste (AREA)
EP95810763A 1994-12-24 1995-12-05 Brennkammer Expired - Lifetime EP0718561B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4446541A DE4446541A1 (de) 1994-12-24 1994-12-24 Brennkammer
DE4446541 1994-12-24

Publications (3)

Publication Number Publication Date
EP0718561A2 EP0718561A2 (de) 1996-06-26
EP0718561A3 EP0718561A3 (de) 1997-04-23
EP0718561B1 true EP0718561B1 (de) 2001-03-14

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EP95810763A Expired - Lifetime EP0718561B1 (de) 1994-12-24 1995-12-05 Brennkammer

Country Status (6)

Country Link
EP (1) EP0718561B1 (zh)
JP (1) JPH08226649A (zh)
KR (1) KR960024018A (zh)
CN (1) CN1133393A (zh)
CA (1) CA2164482A1 (zh)
DE (2) DE4446541A1 (zh)

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DE102005034429A1 (de) * 2005-07-14 2007-02-01 Enbw Kraftwerke Ag Feuerraum
DE102005059184B3 (de) * 2005-12-02 2007-09-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Vorrichtung und Verfahren zur Dämpfung thermoakustischer Resonanzen in Brennkammern

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DE19649486A1 (de) * 1996-11-29 1998-06-04 Abb Research Ltd Brennkammer
DE19654741A1 (de) * 1996-12-30 1998-07-02 Abb Research Ltd Kesselanlage für eine Wärmeerzeugung
DE19728375A1 (de) * 1997-07-03 1999-01-07 Bmw Rolls Royce Gmbh Betriebsverfahren für eine axial gestufte Brennkammer einer Fluggasturbine
JP4508474B2 (ja) * 2001-06-07 2010-07-21 三菱重工業株式会社 燃焼器
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WO2007113074A1 (de) * 2006-03-31 2007-10-11 Alstom Technology Ltd Brennstofflanze für eine gasturbinenanlage sowie ein verfahren zum betrieb einer brennstofflanze
JP2009156542A (ja) * 2007-12-27 2009-07-16 Mitsubishi Heavy Ind Ltd ガスタービンの燃焼器
EP2112433A1 (en) 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Mixing chamber
EP2230455B1 (en) * 2009-03-16 2012-04-18 Alstom Technology Ltd Burner for a gas turbine and method for locally cooling a hot gases flow passing through a burner
EP2253888B1 (en) * 2009-05-14 2013-10-16 Alstom Technology Ltd Burner of a gas turbine having a vortex generator with fuel lance
US20120304652A1 (en) * 2011-05-31 2012-12-06 General Electric Company Injector apparatus
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CN108088236A (zh) * 2018-01-18 2018-05-29 南京苏冶钙业技术有限公司 工业煅烧立窑
CN110748920B (zh) * 2018-07-23 2024-02-09 中国联合重型燃气轮机技术有限公司 轴向分级燃烧器
CN109668172B (zh) * 2018-12-10 2020-11-10 中国航天空气动力技术研究院 一种可控脉动涡流的高速燃油掺混器
FR3106653B1 (fr) * 2020-01-23 2022-01-07 Safran Aircraft Engines Ensemble pour une turbomachine
KR20220153655A (ko) * 2020-03-31 2022-11-18 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 버너의 버너 구성요소 및 이러한 유형의 버너 구성요소를 갖는 가스 터빈의 버너
CN112228905B (zh) * 2020-10-13 2022-01-21 西北工业大学 一种可抑制超临界流体流量分配偏差的通道结构
KR102382634B1 (ko) * 2020-12-22 2022-04-01 두산중공업 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
US11454396B1 (en) * 2021-06-07 2022-09-27 General Electric Company Fuel injector and pre-mixer system for a burner array
CN115127121B (zh) * 2022-06-15 2024-01-12 北京航空航天大学 稳焰预混燃烧装置及航空发动机模拟试验设备

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EP0694740A2 (de) * 1994-07-25 1996-01-31 Abb Research Ltd. Brennkammer

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DE102005034429A1 (de) * 2005-07-14 2007-02-01 Enbw Kraftwerke Ag Feuerraum
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Also Published As

Publication number Publication date
CN1133393A (zh) 1996-10-16
CA2164482A1 (en) 1996-06-25
KR960024018A (ko) 1996-07-20
DE59509091D1 (de) 2001-04-19
DE4446541A1 (de) 1996-06-27
EP0718561A2 (de) 1996-06-26
JPH08226649A (ja) 1996-09-03
EP0718561A3 (de) 1997-04-23

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