EP0718561A2 - Brûleur - Google Patents

Brûleur Download PDF

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Publication number
EP0718561A2
EP0718561A2 EP95810763A EP95810763A EP0718561A2 EP 0718561 A2 EP0718561 A2 EP 0718561A2 EP 95810763 A EP95810763 A EP 95810763A EP 95810763 A EP95810763 A EP 95810763A EP 0718561 A2 EP0718561 A2 EP 0718561A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
stage
flow
channel
fuel
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.)
Granted
Application number
EP95810763A
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German (de)
English (en)
Other versions
EP0718561B1 (fr
EP0718561A3 (fr
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 Management 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
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Publication of EP0718561A2 publication Critical patent/EP0718561A2/fr
Publication of EP0718561A3 publication Critical patent/EP0718561A3/fr
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Publication of EP0718561B1 publication Critical patent/EP0718561B1/fr
Anticipated expiration legal-status Critical
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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 the preamble of claim 1. It also relates to a method for operating such a combustion chamber.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object of minimizing all pollutant emissions occurring during combustion in a combustion chamber and a method of the type mentioned, regardless of the type of fuel used.
  • the main advantage of the combustion chamber according to the invention is that here two burner characteristics are focused to an inventive combination, with the final purpose, in particular to allow the NOx emissions to strive towards zero. Only part of the combustion air flows through the first part of the combustion chamber, based on a premix combustion, and supplies the hot gas for the downstream second part of the combustion chamber. The total mass flow flows through the second part of the combustion chamber.
  • the aim is to operate the first part of the combustion chamber with the lowest possible temperature in "premix mode" in order to achieve the lowest possible basic NOx level of a few vppm. This is achieved by preheating the temperature of the combustion air in front of the first partial combustion chamber to a temperature in the order of 500-700 ° C.
  • This combustion air can be raised relatively easily from the final compressor temperature to the desired level, preferably by using it beforehand directly as cooling air for the combustion chamber itself or at integrated ones Heat exchanger elements is passed.
  • the hot gases are then brought downstream of the first part of the combustion chamber by wall cooling effects and by injecting the remaining combustion air which was not used in the first part of the combustion chamber to the temperature which comes to self-ignition in the second part of the combustion chamber, this second part of the combustion chamber being equipped with vortex generators, one of which Trigger swirl flow.
  • the second combustion chamber part is operated as a single-stage load combustion chamber, in contrast to the first combustion chamber part, which is operated as an idle combustion chamber.
  • the second combustion chamber part works up to gas temperatures of approx. 1600 ° C due to the extremely good mixture, NOX-neutral and provides a total NOx potential with a very flat temperature / NOx characteristic of 1-2 vppm.
  • Another advantage of the invention is that the ignition delay times for different fuels can be optimally adapted by adapting the temperature at the entry into the second combustion chamber part.
  • 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 consist.
  • the combustion chamber can also consist of a single tube.
  • 1 consists of a first 1 and a second stage 2, which are connected in series, and the second stage 2 also includes the actual combustion zone 11.
  • the first stage 1 in the flow direction initially consists of a number of burners 100 arranged in the circumferential direction, this burner being described further below.
  • the sectional plane shown is used.
  • a compressor 18, not shown, in which the intake air is compressed acts upstream of the burner 100 mentioned.
  • the air then supplied by the compressor has a pressure of 10-40 bar.
  • a portion of 30-60% of the compressed air flows into the burner 100, the mode of operation of which is described in more detail in FIGS. 2-5.
  • this portion of air 115 Prior to the inflow into the burner 100, this portion of air 115 is heated to a temperature of 500-700 ° C. This is done by previously using this air directly as cooling air for the combustion chamber. Another possibility is to let this air 115 flow through heat exchangers, not shown.
  • This preheating and reduced proportion in the first part of the combustion chamber result in very low NOx emissions, in the order of 1-3 vppm.
  • a largely NOx-free hot gas 4 is thus available at the end of this first combustion chamber part 1.
  • the hot gases 4 flow into an inflow zone 5 and there they 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 preferably in this area by wall cooling effects and by injection of the remaining air 17 brought to a temperature of 800-1100 ° C.
  • this injection preferably also being carried out via the vortex generators 200.
  • the total air is then 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 can be designed as a venturi channel, several fuel lances 8 are arranged, which take over the supply of a fuel 9 and a supporting air 10. These media can be fed to the individual fuel lances 8, for example, via a ring line (not shown), and the fuel can also be fed via fuel lances 3 integrated in the vortex generators 200.
  • the swirl flow triggered by the vortex generators 200 ensures a large-scale distribution of the introduced fuel 9, and possibly also the admixed support air 10 to a fuel / air mixture 19. 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. If 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. With such a combustion, as already appreciated above, there is a risk of a flashback.
  • the premixing zone 7 as a venturi channel (not shown in more detail) 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 turbulence is reduced by increasing the axial speed, which reduces the risk of kickback due to the reduction in turbulence Flame speed is minimized.
  • the large-scale distribution of the fuel 9 is still guaranteed, since the peripheral component of the swirl flow originating from the vortex generators 200 is not impaired.
  • 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 occurs in the area 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 reapplication 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 arise due to the negative pressure prevailing there, which then lead to stabilization of the flame front 21.
  • 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 from this turbine can then be used to operate a steam cycle, the switching in the latter case is a combination system.
  • 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 power control via the gas turbine load is essentially carried out by adjusting the amount of fuel in the second stage 2.
  • the first stage 1 is operated as an idle combustion chamber
  • the second stage 2 is operated as a single-stage load combustion chamber.
  • FIGS. 3-5 In order to better understand the structure of the burner 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 burner 100 according to FIG. 2 consists of two hollow, conical partial bodies 101, 102 which are nested in one another so as to be offset.
  • 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 Burner 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 likewise, similarly to the tapered partial bodies 101, 102, are offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the burner 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 predefined parameters of the respective burner 100.
  • the burner 100 can be designed to be 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 placed at the latest at the end of the tangential inflow, before entering the cone cavity 114, in order to obtain an optimal air / fuel mixture.
  • the outlet opening of the burner 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 110 b is supplied to the front part of the inflow zone 5.
  • the fuel brought up through the nozzle 103 is preferably a liquid fuel 112, which may at most be enriched with a recirculated exhaust gas.
  • 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 burner 100 is operated with a gaseous fuel 113, this can also be done via the fuel nozzle 103, but preferably this is 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 burner 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.
  • the conical sub-bodies 101, 102 When designing the conical sub-bodies 101, 102 with respect to the cone angle and the width of the tangential air inlet slots 119, 120, strict limits must be adhered to so that the desired flow field of the combustion air 115 at the burner outlet 100 can set.
  • the critical number of swirls is set at the outlet of burner 100: a backflow zone (vortex breakdown) with a flame-stabilizing effect also forms there.
  • minimizing the cross section of the tangential air inlet slots 119, 120 is predestined to form a backflow zone 106.
  • the design of the burner 100 is furthermore particularly suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operating bandwidth can be recorded without changing the overall length of the burner 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.
  • 3-5 now shows the geometrical configuration of the guide plates 121a, 121b. They 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, in that guide baffles as required form a fixed component with the tapered partial bodies 101, 102. 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 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 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 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 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 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.
  • only one vortex is generated on the arrowed side, as is shown in the figure. Accordingly, there is no vortex-neutral field downstream of this vortex generator, 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 its longitudinal extent in the same channel wall 6 on which the Vortex generators are arranged.
  • the geometry of the wall bores 223 or of the slot 222 is selected such that the fuel is introduced into the main flow 4 at a specific 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 (see above) is initially carried out via guides, not shown introduced through the channel wall 6 into the hollow interior of the vortex generators. 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.
  • the injection takes place via wall bores 227, which are located in the side surfaces 211 and 213, on the one hand in the region of the longitudinal edges 212 and 214, and on the other hand in the region of the connecting edge 216.
  • This variant is similar in effect to that from FIG. 10 (bores 221 ) and from Fig. 15 (bores 226).

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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 Brûleur Expired - Lifetime EP0718561B1 (fr)

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 true EP0718561A2 (fr) 1996-06-26
EP0718561A3 EP0718561A3 (fr) 1997-04-23
EP0718561B1 EP0718561B1 (fr) 2001-03-14

Family

ID=6537077

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810763A Expired - Lifetime EP0718561B1 (fr) 1994-12-24 1995-12-05 Brûleur

Country Status (6)

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

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EP2230455A1 (fr) * 2009-03-16 2010-09-22 Alstom Technology Ltd Brûleur pour une turbine à gaz et procédé de refroidissement local d'un flux de gaz chauds passant par un brûleur
EP2253888A1 (fr) * 2009-05-14 2010-11-24 Alstom Technology Ltd Brûleur d'une turbine à gaz
EP2002185B1 (fr) * 2006-03-31 2016-08-10 Alstom Technology Ltd Lance à combustible pour installation de turbine à gaz et procédé d'utilisation d'une lance à combustible

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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
DE102005034429B4 (de) * 2005-07-14 2007-04-19 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
JP2009156542A (ja) * 2007-12-27 2009-07-16 Mitsubishi Heavy Ind Ltd ガスタービンの燃焼器
US20120304652A1 (en) * 2011-05-31 2012-12-06 General Electric Company Injector apparatus
EP2685163B1 (fr) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
CN108088236B (zh) * 2018-01-18 2024-06-18 南京苏冶钙业技术有限公司 工业煅烧立窑
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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

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1002312A (fr) * 1951-04-01 1952-03-05 Chambre de combustion pour thermo-propulseurs, turbo-moteurs ou analogues
US2999359A (en) * 1956-04-25 1961-09-12 Rolls Royce Combustion equipment of gas-turbine engines
FR2392231A1 (fr) * 1977-05-23 1978-12-22 Inst Francais Du Petrole Turbine a gaz comportant une chambre de combustion entre les etages de la turbine
DE3238685A1 (de) * 1982-10-19 1984-04-19 Kraftwerk Union AG, 4330 Mülheim Gasturbinenbrennkammer
DE3707773C2 (de) * 1987-03-11 1996-09-05 Bbc Brown Boveri & Cie Einrichtung zur Prozesswärmeerzeugung
US4821512A (en) * 1987-05-05 1989-04-18 United Technologies Corporation Piloting igniter for supersonic combustor
US4903480A (en) * 1988-09-16 1990-02-27 General Electric Company Hypersonic scramjet engine fuel injector
US5013236A (en) * 1989-05-22 1991-05-07 Institute Of Gas Technology Ultra-low pollutant emission combustion process and apparatus
CH684960A5 (de) * 1991-12-05 1995-02-15 Asea Brown Boveri Verfahren zur Prozesswärmeerzeugung.
DE4242003A1 (de) * 1992-12-12 1994-06-16 Abb Research Ltd Prozesswärmeerzeuger
DE4302847A1 (de) * 1993-02-02 1994-08-04 Abb Research Ltd Verfahren zur schadstoffarmen 2-Stufen-Verbrennung eines Brennstoffs sowie Vorrichtung zur Durchführung des Verfahrens
DE4304989A1 (de) * 1993-02-18 1994-08-25 Abb Management Ag Verfahren zur Kühlung einer Gasturbinenanlage
CH687831A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Vormischbrenner.
EP0620403B1 (fr) * 1993-04-08 1996-12-04 ABB Management AG Dispositif de mélange et de stabilisation de la flamme dans une chambre de combustion avec mélange préalable du combustible.
CH687269A5 (de) * 1993-04-08 1996-10-31 Abb Management Ag Gasturbogruppe.
DE59402803D1 (de) * 1993-04-08 1997-06-26 Asea Brown Boveri Brennkammer
EP0619133B1 (fr) * 1993-04-08 1996-11-13 ABB Management AG Chambre de mélanges
CH687832A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Brennstoffzufuehreinrichtung fuer Brennkammer.
DE4426351B4 (de) * 1994-07-25 2006-04-06 Alstom Brennkammer für eine Gasturbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004090305A1 (fr) * 2003-04-07 2004-10-21 Prodrive 2000 Limited Unite de combustion pour turbocompresseur
EP2002185B1 (fr) * 2006-03-31 2016-08-10 Alstom Technology Ltd Lance à combustible pour installation de turbine à gaz et procédé d'utilisation d'une lance à combustible
EP2112433A1 (fr) * 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
US8424310B2 (en) 2008-04-23 2013-04-23 Siemens Aktiengesellschaft Mixing chamber
EP2230455A1 (fr) * 2009-03-16 2010-09-22 Alstom Technology Ltd Brûleur pour une turbine à gaz et procédé de refroidissement local d'un flux de gaz chauds passant par un brûleur
US8850788B2 (en) 2009-03-16 2014-10-07 Alstom Technology Ltd Burner including non-uniformly cooled tetrahedron vortex generators and method for cooling
EP2253888A1 (fr) * 2009-05-14 2010-11-24 Alstom Technology Ltd Brûleur d'une turbine à gaz
US9726377B2 (en) 2009-05-14 2017-08-08 Ansaldo Energia Switzerland AG Burner of a gas turbine

Also Published As

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EP0718561B1 (fr) 2001-03-14
CA2164482A1 (fr) 1996-06-25
DE59509091D1 (de) 2001-04-19
CN1133393A (zh) 1996-10-16
DE4446541A1 (de) 1996-06-27
EP0718561A3 (fr) 1997-04-23
JPH08226649A (ja) 1996-09-03
KR960024018A (ko) 1996-07-20

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