EP0623786A1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP0623786A1
EP0623786A1 EP94103551A EP94103551A EP0623786A1 EP 0623786 A1 EP0623786 A1 EP 0623786A1 EP 94103551 A EP94103551 A EP 94103551A EP 94103551 A EP94103551 A EP 94103551A EP 0623786 A1 EP0623786 A1 EP 0623786A1
Authority
EP
European Patent Office
Prior art keywords
channel
combustion chamber
vortex
chamber according
flow
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
EP94103551A
Other languages
German (de)
English (en)
Other versions
EP0623786B1 (fr
Inventor
Rolf Dr. Althaus
Alexander Dr. Beeck
Yau-Pin Dr. Chyou
Adnan Eroglu
Burkhard Dr. Schulte-Werning
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ABB AG Germany
Original Assignee
ABB 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
Application filed by ABB Management AG filed Critical ABB Management AG
Publication of EP0623786A1 publication Critical patent/EP0623786A1/fr
Application granted granted Critical
Publication of EP0623786B1 publication Critical patent/EP0623786B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/408—Flow influencing devices in the air tube
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/30—Injector mixers
    • B01F25/31—Injector mixers in conduits or tubes through which the main component flows
    • B01F25/313—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
    • B01F25/3131—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit with additional mixing means other than injector mixers, e.g. screens, baffles or rotating elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/4317—Profiled elements, e.g. profiled blades, bars, pillars, columns or chevrons
    • B01F25/43171—Profiled blades, wings, wedges, i.e. plate-like element having one side or part thicker than the other
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/43197—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor characterised by the mounting of the baffles or obstructions
    • B01F25/431971—Mounted on the wall
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/434—Mixing tubes comprising cylindrical or conical inserts provided with grooves or protrusions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/02—Influencing flow of fluids in pipes or conduits
    • 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
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/4317—Profiled elements, e.g. profiled blades, bars, pillars, columns or chevrons

Definitions

  • the invention relates to a combustion chamber in which a gaseous or liquid fuel is injected as a secondary flow into a gaseous, channeled main flow, the secondary flow having a substantially smaller mass flow than the main flow.
  • a delta wing that is employed in a channelized flow can be regarded as a vortex generator in the broadest sense. If such wings are flown from the tip, a dead water area is created on the one hand downstream of the wing, and on the other hand the flow through the employed surface experiences a not inconsiderable drop in pressure.
  • the arrangement of such a delta wing in a channel must be carried out using flow-restricting aids such as struts, ribs or the like. Furthermore result there are problems with the cooling of such elements, for example in a hot gas flow.
  • Such delta wings cannot be used as mixing elements of two or more flows.
  • the mixing of a secondary flow with a main flow present in a channel usually takes place by radial injection of the secondary flow into the channel.
  • the momentum of the secondary flow is so small, however, that an almost complete mixing only takes place after a distance of approx. 100 channel heights.
  • the invention is therefore based on the object of providing a combustion chamber of the type mentioned at the outset with a device with which longitudinal vortices can be generated in the channel through which flow occurs without a recirculation area.
  • this is achieved in that the main flow is conducted via vortex generators, of which several are arranged next to one another over the width or the circumference of the flow-through channel, preferably without gaps, and the height of which is at least 50% of the height of the flow-through channel or that Vortex generator associated channel part, and that the secondary flow is introduced into the channel in the immediate area of the vortex generators.
  • vortex generators of which several are arranged next to one another over the width or the circumference of the flow-through channel, preferably without gaps, and the height of which is at least 50% of the height of the flow-through channel or that Vortex generator associated channel part, and that the secondary flow is introduced into the channel in the immediate area of the vortex generators.
  • the advantage of such an element can be seen in its particular simplicity in every respect.
  • the element consisting of three walls with flow around it is completely problem-free.
  • the roof surface can be joined with the two side surfaces in a variety of ways.
  • the element can also be fixed to flat or curved channel walls in the case of weldable materials by simple weld seams. From a fluidic point of view, the element has a very low pressure drop when flowing around and it creates vortices without a dead water area.
  • the element due to its generally hollow interior, the element can be cooled in a variety of ways and with various means.
  • the two side surfaces enclosing the arrow angle ⁇ form an at least approximately sharp connecting edge with one another, which together with the longitudinal edges of the roof surface forms a tip, the flow cross-section is hardly impaired by blocking.
  • the sharp connecting edge is the exit-side edge of the vortex generator and it runs perpendicular to the channel wall with which the side surfaces are flush, then the non-formation of a wake area achieved thereby is advantageous.
  • a vertical connecting edge also leads to side surfaces that are also perpendicular to the channel wall, which gives the vortex generator the simplest possible form that is most favorable in terms of production technology.
  • a vortex generator two generated the same opposite vortex.
  • the angle of attack ⁇ of the roof surface and / or the arrow angle ⁇ of the side surfaces are selected such that the vortex generated by the flow bursts in the region of the vortex generator.
  • FIGS. 1, 5 and 6 do not show the actual channel through which a main flow symbolized by a large arrow flows.
  • a vortex generator essentially consists of three free-flowing triangular surfaces. These are a roof surface 10 and two side surfaces 11 and 13. In their longitudinal extent, these surfaces run at certain angles in the direction of flow.
  • the two side surfaces 11 and 13 are perpendicular to the channel wall 21, it being noted that this is not mandatory.
  • the side walls which consist of right-angled triangles, are fixed with their long sides on this channel wall 21, 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 16 and is also perpendicular to the channel wall 21 with which the side surfaces are flush.
  • the two side surfaces 11, 13 including the arrow angle ⁇ are symmetrical in shape, size and orientation and are arranged on both sides of an axis of symmetry 17 (FIGS. 3b, 4b). This axis of symmetry 17 is rectified like the channel axis.
  • the roof surface 10 lies against the same channel wall 21 as the side walls 11, 13 with an edge 15 which runs across the channel and is very pointed.
  • the vortex generator can also be provided with a bottom surface with which it is fastened in a suitable manner to the channel wall 21.
  • a floor area is not related to the mode of operation of the element.
  • the connecting edge 16 of the two side surfaces 11, 13 forms the downstream edge of the vortex generator.
  • the edge 15 of the roof surface 10 which runs transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • the vortex generator works as follows: When flowing around edges 12 and 14, the main flow is converted into a pair of opposing vortices. Their vortex axes lie in the axis of the main flow. The number of swirls and the location of the vortex breakdown (if the latter is desired at all) are determined by appropriate selection of the angle of attack ⁇ and the arrow angle ⁇ . With increasing angles, the vortex strength or the number of swirls is increased and the location of the vortex bursting moves upstream into the area of the vortex generator itself. Depending on the application, these two angles ⁇ and ⁇ are predetermined by the structural conditions and by the process itself. Only the length L of the element (FIG. 3b) and the height h of the connecting edge 16 (FIG. 3a) then have to be adjusted.
  • FIGS. 3a and 4a in which the channel through which flow is indicated is 20, it can be seen that the vortex generator can have different heights compared to the channel height H.
  • the height h of the connecting edge 16 will be coordinated with the channel height H in such a way that the vortex generated immediately downstream of the vortex generator already has such a size that the full channel height H is filled, which results in a uniform velocity distribution in the applied Cross section leads.
  • Another criterion that can influence the ratio h / H to be selected is the pressure drop that occurs when the vortex generator flows around. It goes without saying that the pressure loss coefficient also increases with a larger ratio h / H.
  • the sharp connecting edge 16 in FIG. 2 is the point which is first acted upon by the channel flow.
  • the element is rotated by 180 °.
  • the two opposite vortices have changed their sense of rotation.
  • Fig. 3 it is shown how several, here 3 vortex generators are arranged side by side without gaps across the width of the flow channel 20.
  • the channel 20 has a rectangular shape in this case, but this is not essential to the invention.
  • FIG. 4 An embodiment variant with two full and two half vortex generators adjoining it on both sides is shown in FIG. 4.
  • the elements differ in particular by their greater height h. If the angle of attack remains the same, this inevitably leads to a greater length L of the element and consequently - because of the same division - to a smaller arrow angle ⁇ .
  • the vortices generated will have a lower swirl strength, but will fill the channel cross section completely within a shorter interval. If in In both cases a vortex burst is intended, for example to stabilize the flow, this will take place later in the vortex generator according to FIG. 4 than in that according to FIG. 3.
  • the channels shown in FIGS. 3 and 4 represent rectangular combustion chambers. It is pointed out once again that the shape of the channel through which flow passes is not essential for the mode of operation of the invention. Instead of the rectangle shown, the channel could also be a ring segment, i.e. the walls 21a and 21b would be curved. In such a case, the above statement that the side surfaces are perpendicular to the channel wall must of course be relativized. It is important that the connecting edge 16 lying on the line of symmetry 17 is perpendicular to the corresponding wall. In the case of annular walls, the connecting edge 16 would thus be aligned radially, as is shown in FIG. 7.
  • FIGS. 7 and 8 show in simplified form a combustion chamber with an annular flow through channel 20.
  • an equal number of vortex generators are lined up in the circumferential direction in such a way that the connecting edges 16 of two opposite vortex generators lie in the same radial .
  • FIG. 7 shows that the vortex generators on the inner channel ring 21b have a smaller arrow ⁇ .
  • ⁇ In the longitudinal section in FIG. 8 it can be seen that this could be compensated for by a larger angle of attack ⁇ if swirl-like vortices in the inner and outer ring cross-section are desired.
  • two vortex pairs are generated, each with smaller vertebrae, which leads to a shorter mixing length.
  • the fuel could be in this version according to the methods of 5 or 6 to be described later are introduced into the main flow.
  • the secondary flow in the form of a liquid fuel, for example, has a substantially smaller mass flow than the main flow. It is introduced vertically into the main flow in the immediate area of the vortex generators.
  • this injection takes place via individual bores 22a, which are made in the wall 21a.
  • the wall 21a is the wall on which the vortex generators are arranged.
  • the bores 22a are located on the line of symmetry 17 downstream behind the connecting edge 16 of each vortex generator. With this configuration, the fuel is fed into the already existing large-scale vortices.
  • FIG. 4 shows an embodiment variant of a combustion chamber in which the secondary flow is also injected via wall bores 22b. These are located downstream of the vortex generators in that wall 21b on which the vortex generators are not arranged, that is to say on the wall opposite the wall 21a.
  • the wall bores 22b are each made centrally between the connecting edges 16 of two adjacent vortex generators, as can be seen in FIG. 4. In this way, the fuel reaches the vortex in the same way as in the embodiment according to FIG. 3, but with the difference that it is no longer mixed into the vortex of a pair of vertebrae produced by the same vortex generator, but in one each Vortex of two neighboring vortex generators. Because the neighboring vortex generators Meanwhile, are arranged without a space and produce vortex pairs with the same direction of rotation, the injections according to FIGS. 3 and 4 have the same effect.
  • FIGS. 5 and 6 show further possible forms of introducing the secondary flow into the main flow.
  • the secondary flow is introduced here through means not shown through the channel wall 21 into the hollow interior of the vortex generator.
  • the secondary flow is injected into the main flow via a wall bore 22e, the bore being arranged in the region of the tip 18 of the vortex generator.
  • the injection takes place via wall bores 22d, which are located in the side surfaces 11 and 13 on the one hand in the region of the longitudinal edges 12 and 14 and on the other hand in the region of the connecting edge 16.
  • FIGS. 9 to 14 show different installation options for the vortex generators.
  • FIG. 9 shows an annular channel 20 in which an equal number of vortex generators 9 are lined up in the circumferential direction both on the outer ring wall 21a and on the inner ring wall 21b. 7, however, the connecting edges 16 of two opposite vortex generators are offset by half a division. This arrangement offers the possibility of increasing the height h of the individual element. Downstream of the vortex generators, the generated vortexes are combined with one another, which on the one hand improves the mixing quality and on the other hand leads to a longer lifespan of the vortex.
  • the ring channel is segmented by means of radially extending ribs 23.
  • a vortex generator 9 is arranged on the ribs 23 in each of the circular ring segments formed in this way.
  • the two vortex generators are designed to fill the entire channel height. This solution simplifies the fuel supply that can be made through the hollow ribs. This means that there is no impairment of the flow by centrally arranged fuel lances.
  • vortex generators are also attached to the ring walls 21a and 21b.
  • the connecting edges of the side elements run at half the channel height, those of the upper and lower in a radial at half the segment width. In terms of how it works, this is a very good solution.
  • the elements here cannot fill the entire channel height. It is therefore not to be overlooked that the cooling that may be required is structurally complex, since cooling air supply from the ring walls is not readily possible for the lateral elements.
  • the vortex generators 9 in FIG. 12 are arranged off-center on the radial ribs 23 and on the ring walls 21a, 21b.
  • One side surface of each vortex generator lies against a corner of the circular ring segment, from where the lateral vortex generators can also be supplied with cooling air from the radially outer ring wall 21a, on the one hand, and from the inner ring wall 21b, on the other hand.
  • FIG. 13 Another embodiment according to FIG. 13 is also in respect of a simple cooling possibility Segment of the circular channel, the vortex generators 9 are arranged directly in the segment corners.
  • FIGS. 6, 11 and 14 show an additional central introduction of the secondary flow in a mixed arrangement of the variants dealt with in FIGS. 6, 11 and 14.
  • the fuel usually oil
  • vortex generators of different geometries are used in the rectangular channel, which of course could just as well be a circular ring segment.
  • the vortex generators that follow one another in the “circumferential direction” are slightly offset from one another. This, for example, to create the required space for the lance.
  • the secondary flow is partially injected via wall holes in the side surfaces of the vortex generators, as indicated by arrows.
  • the gas supply takes place via gas lines 25 running along the wall.
  • gas lines 25 running along the wall.
  • a combustion chamber has become good for dual operation with premix combustion own.
  • the mixture is ignited 26 at the point at which the vortex bursts (vortex break down).
  • a diffuser 27 is arranged in the plane behind the mixing zone at which the ignition takes place. The good temperature distribution downstream of the vortex generators achieved as a result of the mixing elements avoids the risk of reignition, which is possible without the measure for introducing cooling air into the combustion air mentioned at the beginning.
  • the combustion chamber just described could also be a self-igniting post-combustion chamber downstream of a high-temperature gas turbine.
  • the high energy content of their exhaust gases enables self-ignition. Effective, rapid mixing of the hot gas flow with the injected fuel is a prerequisite for optimizing the combustion process, particularly with regard to minimizing emissions.
  • the vortex generators are designed in such a way that recirculation zones are largely avoided.
  • the residence time of the fuel particles in the hot zones is very short, which has a favorable effect on the minimal formation of NO x .
  • the injected fuel is dragged along by the vortices and mixed with the main flow. It follows the helical course of the vertebrae and is evenly finely distributed in the chamber downstream of the vertebrae. This reduces the risk of impinging jets on the opposite wall and the formation of so-called "hot spots" - in the case of the radial injection of fuel into an undisturbed flow mentioned above.
  • the fuel injection can be kept flexible and adapted to other boundary conditions. In this way, the same injection pulse can be maintained throughout the load range. Since the mixing is determined by the geometry of the vortex generators and not by the machine load, in the example the gas turbine output, the afterburner configured in this way works optimally even under partial load conditions.
  • the combustion process is optimized by adjusting the ignition delay time of the fuel and mixing time of the vortices, which ensures a minimization of emissions.
  • the effective mixing results in a good temperature profile over the cross section through which the flow is flowing and also reduces the possibility of the occurrence of thermoacoustic instability. Due to their presence alone, the vortex generators act as a damping measure against thermoacoustic vibrations.
  • FIGS. 16 and 17 show a top view of an embodiment variant of the vortex generator and a front view of its arrangement in a circular channel.
  • the two side surfaces 11 and 13 enclosing the arrow angle ⁇ have a different length.
  • the vortex generator then naturally has a different angle of attack stell across its width.
  • Such a variant has the effect that vortices with different strengths are generated. For example, this can act on a swirl adhering to the main flow. Or else through the different eddies it becomes original a swirl-free main flow downstream of the vortex generators, as indicated in FIG. 17.
  • Such a configuration works well as an independent, compact burner unit.
  • the swirl imposed on the main flow can be used to improve the cross-ignition behavior of the burner configuration, for example at partial load.
  • the invention is not limited to the examples described and shown. With regard to the arrangement of the vortex generators in the network, many combinations are possible without leaving the scope of the invention.
  • the introduction of the secondary flow into the main flow can also be carried out in a variety of ways.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Dispersion Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
EP94103551A 1993-04-08 1994-03-09 Chambre de combustion Expired - Lifetime EP0623786B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH107893 1993-04-08
CH1078/93 1993-04-08

Publications (2)

Publication Number Publication Date
EP0623786A1 true EP0623786A1 (fr) 1994-11-09
EP0623786B1 EP0623786B1 (fr) 1997-05-21

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EP94103551A Expired - Lifetime EP0623786B1 (fr) 1993-04-08 1994-03-09 Chambre de combustion

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US (1) US5513982A (fr)
EP (1) EP0623786B1 (fr)
JP (1) JP3527280B2 (fr)
DE (1) DE59402803D1 (fr)

Cited By (18)

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EP0675322A2 (fr) * 1994-04-02 1995-10-04 ABB Management AG Brûleur à prémélange
DE19527452A1 (de) * 1995-07-27 1997-01-30 Abb Management Ag Mehrstufige Dampfturbine
DE19536672A1 (de) * 1995-09-30 1997-04-03 Abb Research Ltd Verfahren und Vorrichtung zur Verbrennung von Brennstoffen
EP0718561A3 (fr) * 1994-12-24 1997-04-23 Abb Management Ag Brûleur
EP0776689A1 (fr) * 1995-12-01 1997-06-04 Abb Research Ltd. Dispositif de mélange
WO1998028574A2 (fr) * 1996-12-20 1998-07-02 Siemens Aktiengesellschaft Bruleur pour solides fluides, procede pour actionner un bruleur et element de tourbillonnement
EP0924462A1 (fr) 1997-12-15 1999-06-23 Asea Brown Boveri AG Brûleur pour le fonctionnement d'un générateur de chaleur
US6572366B2 (en) 2001-06-09 2003-06-03 Alstom (Switzerland) Ltd Burner system
EP1382379A2 (fr) * 2002-07-20 2004-01-21 ALSTOM (Switzerland) Ltd Générateur de tourbillons avec contrôle de fluide en aval
DE10250208A1 (de) * 2002-10-28 2004-06-03 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
WO2007067085A1 (fr) * 2005-12-06 2007-06-14 Siemens Aktiengesellschaft Procédé et appareil de combustion d’un carburant
EP2116766A1 (fr) 2008-05-09 2009-11-11 ALSTOM Technology Ltd Lance à combustible
EP2199674A1 (fr) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brûleur d'une turbine à gaz
EP2261566A1 (fr) * 2009-05-28 2010-12-15 Siemens AG Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur
EP2522912A1 (fr) * 2011-05-11 2012-11-14 Alstom Technology Ltd Redresseur de flux et mélangeur
WO2014029512A2 (fr) 2012-08-24 2014-02-27 Alstom Technology Ltd Combustion séquentielle à mélangeur de gaz de dilution
EP2728258A1 (fr) * 2012-11-02 2014-05-07 Alstom Technology Ltd Turbine à gaz
US11454396B1 (en) 2021-06-07 2022-09-27 General Electric Company Fuel injector and pre-mixer system for a burner array

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CH687832A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Brennstoffzufuehreinrichtung fuer Brennkammer.
GB2297151B (en) * 1995-01-13 1998-04-22 Europ Gas Turbines Ltd Fuel injector arrangement for gas-or liquid-fuelled turbine
DE19510744A1 (de) * 1995-03-24 1996-09-26 Abb Management Ag Brennkammer mit Zweistufenverbrennung
DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer
DE19757189B4 (de) * 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
DE19820992C2 (de) * 1998-05-11 2003-01-09 Bbp Environment Gmbh Vorrichtung zur Durchmischung eines einen Kanal durchströmenden Gasstromes und Verfahren unter Verwendung der Vorrichtung
EP1048898B1 (fr) * 1998-11-18 2004-01-14 ALSTOM (Switzerland) Ltd Brûleur
GB0219461D0 (en) * 2002-08-21 2002-09-25 Rolls Royce Plc Fuel injection arrangement
US6886342B2 (en) * 2002-12-17 2005-05-03 Pratt & Whitney Canada Corp. Vortex fuel nozzle to reduce noise levels and improve mixing
WO2005043037A1 (fr) * 2003-10-21 2005-05-12 Petroleum Analyzer Company, Lp Appareil de combustion ameliore et procedes de fabrication et d'utilisation correspondants
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DE102007014226B4 (de) * 2007-03-24 2014-02-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren und Vorrichtung zur Homogenisierung einer Einlaufströmung in einen fächerförmigen Einlauf mit einem flachen Eingangsquerschnitt
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EP1382379A3 (fr) * 2002-07-20 2004-05-12 ALSTOM Technology Ltd Générateur de tourbillons avec contrôle de fluide en aval
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DE10250208A1 (de) * 2002-10-28 2004-06-03 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
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EP2116766A1 (fr) 2008-05-09 2009-11-11 ALSTOM Technology Ltd Lance à combustible
US9097426B2 (en) 2008-05-09 2015-08-04 Alstom Technology Ltd Burner and fuel lance for a gas turbine installation
US8938968B2 (en) 2008-12-19 2015-01-27 Alstom Technology Ltd. Burner of a gas turbine
EP2199674A1 (fr) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brûleur d'une turbine à gaz
WO2010136300A3 (fr) * 2009-05-28 2011-01-27 Siemens Aktiengesellschaft Brûleur et procédé pour réduire des oscillations de flammes auto-induites dans un brûleur
EP2261566A1 (fr) * 2009-05-28 2010-12-15 Siemens AG Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur
EP2522912A1 (fr) * 2011-05-11 2012-11-14 Alstom Technology Ltd Redresseur de flux et mélangeur
US8938971B2 (en) 2011-05-11 2015-01-27 Alstom Technology Ltd Flow straightener and mixer
WO2014029512A2 (fr) 2012-08-24 2014-02-27 Alstom Technology Ltd Combustion séquentielle à mélangeur de gaz de dilution
US9890955B2 (en) 2012-08-24 2018-02-13 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
US10634357B2 (en) 2012-08-24 2020-04-28 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
EP2728258A1 (fr) * 2012-11-02 2014-05-07 Alstom Technology Ltd Turbine à gaz
US11454396B1 (en) 2021-06-07 2022-09-27 General Electric Company Fuel injector and pre-mixer system for a burner array

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DE59402803D1 (de) 1997-06-26
JP3527280B2 (ja) 2004-05-17
JPH06323540A (ja) 1994-11-25
US5513982A (en) 1996-05-07
EP0623786B1 (fr) 1997-05-21

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