EP0694740A2 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP0694740A2
EP0694740A2 EP95810442A EP95810442A EP0694740A2 EP 0694740 A2 EP0694740 A2 EP 0694740A2 EP 95810442 A EP95810442 A EP 95810442A EP 95810442 A EP95810442 A EP 95810442A EP 0694740 A2 EP0694740 A2 EP 0694740A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
channel
flow
fuel
stage
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Withdrawn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
EP95810442A
Other languages
German (de)
English (en)
Inventor
Thomas Dr. Sattelmayer
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 Research Ltd Switzerland
ABB Research Ltd Sweden
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP0694740A2 publication Critical patent/EP0694740A2/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • 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
    • F23C6/042—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with fuel supply in stages
    • 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
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
    • 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
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/222—Improvement of heat transfer by creating turbulence
    • 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
    • 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
    • F23C2900/13002—Catalytic combustion followed by a homogeneous combustion phase or stabilizing a homogeneous combustion phase
    • 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 the preamble of claim 1.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object, in a combustion chamber of the type mentioned, to minimize all pollutant emissions occurring during combustion, regardless of the type of fuel used.
  • the aim here is to keep the mixture constant in the first stage so that UHC and CO emissions can be prevented.
  • the mixer used in the first stage mixes fuel and air evenly, whereby in the case of oil, droplet evaporation takes place. If a premix burner according to EP-A1-0 321 809 is used for the above-mentioned mixing, then this undergoes a modification regarding the aerodynamics, which is manifested in the fact that the swirl is significantly reduced. This is done by 20-100% wider air inlet slots, or by increasing the number of these slots.
  • the new premix burner is characterized by the fact that it is used alone as a mixer and is no longer able to create a backflow zone.
  • this mixer Downstream of this mixer is a catalytic converter in which the fuel / air mixture is completely burned.
  • the mixture is selected in such a way that typical adiabatic flame temperatures between 800 ° and 1100 ° C are reached, thus precluding thermal destruction of the catalyst is. This is a great advantage compared to other catalytic processes for high temperatures. Due to the low temperatures, there is no homogeneous gas phase reaction, but only a reaction on the active surfaces. The NOx production of such a chemical reaction is very low, much less than 1 ppmv. A largely NOx-free hot gas is available at the end of the catalyst.
  • Vortex generators ensure a vortex-intensive flow in order to mix in the fuel injected downstream as quickly as possible.
  • the constant temperature at the entrance to the second stage ensures that the mixture ignites independently of the amount of fuel injected into the second stage.
  • Another important advantage of the invention is that the power control over the gas turbine load can be carried out essentially by adjusting the amount of fuel in the second stage.
  • annular combustion chamber which essentially has the shape of a coherent annular or quasi-annular cylinder.
  • a combustion chamber can also consist of a number of axially, quasi-axially or helically arranged and individually closed combustion chambers.
  • the combustion chamber can also consist of a single one Pipe exist. 1 consists of a first 1 and a second stage 2, which are connected in series, and the second stage 2 consists of the actual combustion zone 11.
  • the first stage 1 in the direction of flow initially consists of a number of mixers 100 arranged in the circumferential direction, the mixer itself being essentially derived from the burner according to EP-0 321 809.
  • a compressor 18 acts in this mixer 100, in which the intake air 17 is compressed.
  • the air 115 then supplied by the compressor has a pressure of 10-40 bar at a temperature of 300-600 ° C.
  • This air 115 flows into the mixer 100, the mode of operation of which is described in more detail in FIGS. 2-5.
  • the fuel / air mixture 19 provided in the mixer 100 reaches a catalyst 3, in which this mixture 19 is completely combusted.
  • the mixture 19 is selected such that typical adiabatic flame temperatures between 800 and 1050 ° C. are reached, with the result that the thermal destruction of the catalyst 3 is excluded. Because of the relatively low temperature, there is no homogeneous gas phase reaction, but only a reaction on the active surfaces of the catalyst 3. The NOx production of such a chemical reaction is very low, much less than 1 ppmv. A largely NOx-free hot gas 4 is thus available at the end of the catalyst 3.
  • the catalyst 3 itself consists of a first very active stage, which initiates the fuel conversion. A palladium oxide is preferably used as the material here. The next stages of the catalyst 3 can consist of other materials, for example of platinum.
  • the flow velocity in the Catalyst 3 is less than about 30 m / s.
  • the hot gases 4 flow into an inflow zone 5 and are accelerated to approximately 80-120 m / s.
  • the inflow zone 5 is equipped on the inside and in the circumferential direction of the channel wall 6 with a series of vortex-generating elements 200, hereinafter only called vortex generators, which will be discussed in more detail below.
  • the hot gases 4 are swirled by the vortex generators 200 such that no recirculation areas occur in the wake of the vortex generators 200 mentioned in the subsequent premixing section 7.
  • this premixing section 7 which is designed as a Venturi channel, a plurality of fuel lances 8 are arranged, which take over the supply of a fuel 9 and supporting air 10. These media can be supplied to the individual fuel lances 8, for example, via a ring line (not shown).
  • the swirl flow triggered by the vortex generators 200 ensures a large-scale distribution of the introduced fuel 9, if necessary also the admixed supporting air 10. Furthermore, the swirl flow ensures a homogenization of the mixture of combustion air and fuel.
  • the fuel 9 injected into the hot gases 4 by the fuel lance 8 triggers self-ignition, provided that these hot gases 4 have the specific temperature which the fuel-dependent auto-ignition can trigger.
  • the ring combustion chamber is operated with a gaseous fuel, a temperature of the hot gases 4 of more than 800 ° C. must be present to initiate self-ignition, which is also present here.
  • a temperature of the hot gases 4 of more than 800 ° C. must be present to initiate self-ignition, which is also present here.
  • This problem is remedied by, on the one hand, designing the premixing zone 7 as a venturi channel and, on the other hand, disposing the injection of the fuel 9 in the region of the largest constriction in the premixing zone 7.
  • the constriction in the premixing zone 7 reduces the turbulence by increasing the axial speed, which minimizes the risk of kickback by reducing the turbulent flame speed.
  • the combustion zone 11 follows the relatively short premixing zone 7.
  • the transition between the two zones is formed by a radial cross-sectional jump 12, which initially indicates the flow cross-section of the combustion zone 11.
  • a flame front 21 also arises in the plane of the cross-sectional jump 12.
  • the vortex generators 200 are designed such that no recirculation takes place in the premixing zone 7; only after the sudden cross-sectional expansion does the swirl flow burst.
  • the swirl flow supports the rapid re-application of the flow behind the cross-sectional jump 12, so that a high burn-out with a short overall length can be achieved by utilizing the volume of the combustion zone 11 as fully as possible.
  • a flow-like edge zone is formed during operation, in which vortex detachments occur due to the prevailing negative pressure, which then lead to stabilization of the flame front.
  • These corner vortices 20 also form the ignition zones within the second stage 2.
  • the hot working gases 13 provided in the combustion zone 11 then act on a downstream turbine 14.
  • the exhaust gases 15 can then be used to operate a steam cycle, in the latter case the switching then Combined system is.
  • the proposed method also behaves very well with regard to a wide load range. Since the mixture in the first stage 1 is always kept largely constant, the UHC or CO emissions can also be prevented.
  • the constant temperature at the entrance to the second stage 2 ensures reliable self-ignition of the mixture, regardless of the amount of fuel in the second stage 2.
  • the inlet temperature is still high enough to achieve sufficient burnout in the second stage 2 even with a small amount of fuel .
  • the output control via the gas turbine load essentially takes place by adapting the fuel quantity in the second stage 2.
  • the controllable compressor 18 ensures that the minimum combustion temperature at the outlet of the catalytic converter 3 is not undercut at zero load.
  • FIGS. 3-5 In order to better understand the structure of the mixer 100, it is advantageous if the individual cuts according to FIGS. 3-5 are used simultaneously with FIG. 2. Furthermore, in order not to make FIG. 2 unnecessarily confusing, the guide plates 121a, 121b shown schematically according to FIGS. 3-5 have only been hinted at. In the description of FIG. 2, reference is made below to the remaining FIGS. 3-5 as required.
  • the mixer 100 consists of two hollow, conical partial bodies 101, 102 which are nested one inside the other.
  • the offset of the respective central axis or longitudinal axis of symmetry 201b, 202b of the conical partial bodies 101, 102 to one another creates a tangential air inlet slot 119, 120 on both sides, in a mirror-image arrangement (FIGS. 3-5), through which the combustion air 115 enters the interior of the Mixer 100, ie flows into the cone cavity 114.
  • the conical shape of the partial bodies 101, 102 shown in the flow direction has a specific fixed angle.
  • the partial bodies 101, 102 can have an increasing or decreasing cone inclination in the direction of flow, similar to a trumpet or. Tulip.
  • the last two forms are not included in the drawing, since they can be easily understood by a person skilled in the art.
  • the two tapered partial bodies 101, 102 each have a cylindrical starting part 101a, 102a, which, similarly to the conical partial bodies 101, 102, also run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the mixer 100.
  • a nozzle 103 is accommodated, the injection 104 of which coincides approximately with the narrowest cross section of the conical cavity 114 formed by the conical partial bodies 101, 102.
  • the injection capacity and the type of this nozzle 103 depend on the specified parameters of the respective mixer 100.
  • the mixer 100 can be designed purely conical, that is to say without cylindrical starting parts 101a, 102a.
  • the conical sub-bodies 101, 102 further each have a fuel line 108, 109, which are arranged along the tangential inlet slots 119, 120 and are provided with injection openings 117, through which a gaseous fuel 113 is preferably injected into the combustion air 115 flowing through there, such as arrows 116 symbolize this.
  • These fuel lines 108, 109 are preferably at the latest at the end of the tangential Inflow, prior to entering the cone cavity 114, is placed in order to obtain an optimal air / fuel mixture.
  • the outlet opening of the mixer 100 merges into a front wall 110, in which a number of bores 110a are provided.
  • the latter come into operation when necessary and ensure that dilution air or cooling air 110b is supplied to the front part of the transition piece 122.
  • the fuel brought in through the nozzle 103 is a liquid fuel 112, which can be enriched with a recirculated exhaust gas at most.
  • This fuel 112 is injected into the cone cavity 114 at an acute angle.
  • a conical fuel profile 105 is thus formed from the nozzle 103 and is enclosed by the rotating combustion air 115 flowing in tangentially. In the axial direction, the concentration of the fuel 112 is continuously reduced to an optimal mixture by the inflowing combustion air 115.
  • the mixer 100 is operated with a gaseous fuel 113, this is preferably done via opening nozzles 117, the formation of this fuel / air mixture taking place directly at the end of the air inlet slots 119, 120.
  • the fuel 112 is injected via the fuel nozzle 103, the optimum, homogeneous fuel concentration over the cross section is achieved at the end of the mixer 100.
  • the combustion air 115 is additionally preheated or enriched with a recirculated exhaust gas, this sustainably supports the evaporation of the liquid fuel 112.
  • the same considerations also apply if, instead of gaseous, liquid fuels are supplied via the lines 108, 109.
  • Another way of preventing the formation of a backflow zone is to increase the number of air inlet slots, and at the same time the number of partial bodies increases accordingly.
  • the axial speed within the mixer 100 can be changed by a corresponding supply, not shown, of an axial combustion air flow.
  • the construction of the mixer 100 is furthermore excellently suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operational bandwidth can be recorded without changing the overall length of the mixer 100.
  • the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which even an overlap thereof can be controlled. It is even possible to interleave the partial bodies 101, 102 in a spiral manner by counter-rotating movement.
  • the guide plates 121a, 121b have a flow introduction function, which, depending on their length, extend the respective end of the tapered partial bodies 101, 102 in the direction of flow relative to the combustion air 115.
  • the channeling of the combustion air 115 into the cone cavity 114 can be optimized by opening or closing the guide plates 121a, 121b around a pivot point 123 located in the region of the entry of this channel into the cone cavity 114, in particular this is necessary if the original gap size of the tangential air inlet slots 119, 120 is to be changed from the above motives.
  • these dynamic arrangements can also be provided statically are formed by the need for baffles as a fixed component with the tapered partial bodies 101, 102.
  • Mixer 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 extent, 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 ⁇ are symmetrical in shape, size and orientation in FIG. 4, they are arranged on both sides of an axis of symmetry 217 which is oriented 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 transversely 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 inclination ⁇ 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 he is suitably attached to the channel wall 6. 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 as follows: When flowing around the edges 212 and 214, the main flow is converted into a pair of opposing vortices, as is schematically outlined in the figures.
  • the vortex axes lie in the axis of the main flow.
  • the number of swirls and the location of the vortex breakdown (vortex breakdown), if the latter is aimed for, are determined by appropriate selection of the angle of attack ⁇ and the arrow angle ⁇ .
  • the vortex strength or the number of swirls is increased, and the location of the vortex bursting shifts upstream into the region of the vortex generator 200, 201, 202 itself.
  • these two angles ⁇ and ⁇ are due to structural conditions and determined by the process itself.
  • These vortex generators only have to be adapted in terms of length and height, as will be explained in more detail below under FIG. 9.
  • the connecting edge 216 of the two side surfaces 211, 213 forms the downstream edge of the vortex generator 200.
  • the edge 215 of the roof surface 210 which runs transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • FIG. 7 shows a so-called half "vortex generator” based on a vortex generator according to FIG. 6.
  • the vortex generator 201 shown here only one of the two side surfaces is provided with the arrow angle ⁇ / 2.
  • the other side surface is straight and oriented in the direction of flow.
  • this vortex generator only one vortex is generated on the arrowed side, as is shown in the figure. Accordingly, it is downstream this vortex generator does not have a vortex-neutral field, but a swirl is forced on the flow.
  • FIG. 8 differs from FIG. 6 in that the sharp connecting edge 216 of the vortex generator 202 is the point which is first acted upon by the channel flow. The element is therefore rotated by 180 °. As can be seen from the illustration, the two opposite vortices have changed their sense of rotation.
  • FIG. 9 shows the basic geometry of a vortex generator 200 installed in a channel 5.
  • the height h of the connecting edge 216 will be coordinated with the channel height H, or the height of the channel part which is assigned to the vortex generator that the vortex generated immediately downstream of the vortex generator 200 already reaches such a size that the full channel height H is filled. This leads to a uniform speed distribution in the cross-section applied.
  • Another criterion that can influence the ratio of the two heights h / H to be selected is the pressure drop that occurs when the vortex generator 200 flows around. It goes without saying that the pressure loss coefficient also increases with a larger ratio h / H.
  • the vortex generators 200, 201, 202 are mainly used when it comes to mixing two flows.
  • the main flow 4 as hot gases attacks the transverse edge 215 or the connecting edge 216 in the direction of the arrow.
  • the secondary flow in the form of a gaseous and / or liquid fuel, which is possibly enriched with a portion of supporting air (see FIG. 1), has a much smaller one Mass flow as the main flow. In the present case, this secondary flow is introduced into the main flow downstream of the vortex generator, as can be seen particularly well from FIG. 1.
  • vortex generators 200 are distributed at a distance over the circumference of the channel 5.
  • the vortex generators can also be strung together in the circumferential direction so that no gaps are left on the channel wall 6.
  • the vortices to be generated are ultimately decisive for the choice of the number and the arrangement of the vortex generators.
  • FIGS. 10-16 show further possible forms of introducing the fuel into the hot gases 4. These variants can be combined in a variety of ways with one another and with a central fuel injection, as can be seen, for example, from FIG. 1.
  • the fuel is also injected via wall bores 221, which are located directly next to the side surfaces 211, 213 and in their longitudinal extent in the same channel wall 6, on the the vortex generators are arranged.
  • the introduction of the fuel through the wall bores 221 gives the generated vortices an additional impulse, which extends the lifespan of the vortex generator.
  • the fuel is injected via a slot 222 or via wall bores 223, both arrangements being located directly in front of the edge 215 of the roof surface 210 running transversely to the flowed channel and in the longitudinal extension thereof in the same channel wall 6 on which the Vortex generators are arranged.
  • the geometry of the wall bores 223 or the slot 222 is selected such that the fuel is introduced into the main flow 4 at a certain injection angle and largely shields the post-placed vortex generator as a protective film against the hot main flow 4 by flow around it.
  • the secondary flow (cf. above) is first introduced into the hollow interior of the vortex generators via guides (not shown) through the channel wall 6. This creates an internal cooling facility for the vortex generators without providing any additional equipment.
  • the fuel is injected via wall bores 224, which are located inside the roof surface 210 directly behind and along the edge 215 running transversely to the flow channel.
  • the vortex generator is cooled here more externally than internally.
  • the emerging secondary flow forms when flowing around the roof surface 210 a protective layer shielding it against the hot main flow 4.
  • the fuel is injected via wall bores 225, which are staggered within the roof surface 210 along the line of symmetry 217.
  • the channel walls 6 are particularly well protected from the hot main flow 4, since the fuel is first introduced on the outer circumference of the vortex.
  • the fuel is injected via wall bores 226, which are located in the longitudinal edges 212, 214 of the roof surface 210.
  • This solution ensures good cooling of the vortex generators, since the fuel escapes from its extremities and thus completely flushes the inner walls of the element.
  • the secondary flow is fed directly into the resulting vortex, which leads to defined flow conditions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP95810442A 1994-07-25 1995-07-05 Chambre de combustion Withdrawn EP0694740A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4426351 1994-07-25
DE4426351A DE4426351B4 (de) 1994-07-25 1994-07-25 Brennkammer für eine Gasturbine

Publications (1)

Publication Number Publication Date
EP0694740A2 true EP0694740A2 (fr) 1996-01-31

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810442A Withdrawn EP0694740A2 (fr) 1994-07-25 1995-07-05 Chambre de combustion

Country Status (5)

Country Link
US (1) US5626017A (fr)
EP (1) EP0694740A2 (fr)
JP (1) JPH08189641A (fr)
CN (1) CN1121570A (fr)
DE (1) DE4426351B4 (fr)

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EP1255080A1 (fr) * 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Brûleur catalytique
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WO2005095855A1 (fr) * 2004-03-30 2005-10-13 Alstom Technology Ltd Dispositif et procede pour stabiliser une flamme
US7069727B2 (en) 2003-02-11 2006-07-04 Alstom Technology Ltd. Method for operating a gas turbo group
EP2071155A2 (fr) * 2007-12-14 2009-06-17 United Technologies Corporation Ensemble formant nacelle ayant des turbulateurs
WO2009109448A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
WO2009109454A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Procédé et ensemble brûleur servant à produire du gaz chaud et utilisation dudit procédé
US8057224B2 (en) * 2004-12-23 2011-11-15 Alstom Technology Ltd. Premix burner with mixing section
US8192147B2 (en) 2007-12-14 2012-06-05 United Technologies Corporation Nacelle assembly having inlet bleed
US8282037B2 (en) 2007-11-13 2012-10-09 United Technologies Corporation Nacelle flow assembly
US8468833B2 (en) 2008-03-07 2013-06-25 Alstom Technology Ltd Burner arrangement, and use of such a burner arrangement
WO2013139914A1 (fr) * 2012-03-23 2013-09-26 Alstom Technology Ltd Dispositif de combustion
EP2700878A3 (fr) * 2012-08-24 2014-03-26 Alstom Technology Ltd Procédé pour mélanger un air de dilution dans un système de combustion séquentielle d'une turbine à gaz
WO2014063835A1 (fr) * 2012-10-24 2014-05-01 Alstom Technology Ltd Combustion séquentielle avec mélangeur de gaz d'appoint
CN105371301A (zh) * 2015-10-08 2016-03-02 北京航空航天大学 一种高温射流点火自稳焰的分级燃烧室
AU2012320439B2 (en) * 2011-10-07 2016-05-19 Wobben Properties Gmbh Method and device for mounting a rotor of a wind energy plant
EP3267107A1 (fr) * 2016-07-08 2018-01-10 Ansaldo Energia IP UK Limited Procédé de commande d'un ensemble de turbine à gaz
EP3889506A1 (fr) * 2020-03-31 2021-10-06 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant
WO2021197654A1 (fr) * 2020-03-31 2021-10-07 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur, et brûleur d'une turbine à gaz présentant un composant de brûleur de ce type

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JPH08189641A (ja) 1996-07-23
CN1121570A (zh) 1996-05-01
US5626017A (en) 1997-05-06
DE4426351A1 (de) 1996-02-01
DE4426351B4 (de) 2006-04-06

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