EP0745809A1 - Générateur de tourbillons pour chambre de combustion - Google Patents

Générateur de tourbillons pour chambre de combustion Download PDF

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Publication number
EP0745809A1
EP0745809A1 EP96810314A EP96810314A EP0745809A1 EP 0745809 A1 EP0745809 A1 EP 0745809A1 EP 96810314 A EP96810314 A EP 96810314A EP 96810314 A EP96810314 A EP 96810314A EP 0745809 A1 EP0745809 A1 EP 0745809A1
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EP
European Patent Office
Prior art keywords
combustion chamber
vortex
channel
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
EP96810314A
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German (de)
English (en)
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EP0745809B1 (fr
Inventor
Burkhard Dr. Schulte-Werning
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General Electric Technology GmbH
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ABB Management AG
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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
    • F23R3/02—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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/26—Controlling the air flow
    • 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
    • F05B2250/00—Geometry
    • 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
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

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 temperature profile flowing over the corresponding burners and in the mixing zone upstream of the turbine must be adjusted to the temperature profile appropriate for the turbine by admixing the mass flow not flowing over the burners.
  • the quality from this admixture is usually controlled via the dimensioning of the cross section and the number of air inlet openings.
  • These air inlet openings which also act as mixed air nozzles, ensure both the necessary depth of penetration of the colder air flowing through there and into the hot gas flow and thus generate the macroscopic turbulence necessary for a quick mixing as well as a sufficient even distribution of the colder air supply over the combustion chamber wall.
  • the invention seeks to remedy this.
  • the invention is based on the object to achieve a combustion chamber and a method of the type mentioned to improve the admixture quality and reduce the calorific load of the combustion chamber, at the same time the object of the invention is to minimize the pollutant - Ensure emissions and maximize efficiency.
  • vortex-generating elements hereinafter referred to only as vortex generators, which are preferably fixed to the combustion chamber wall or the combustion chamber walls in the mixing section, downstream of the primary zone.
  • vortex generators are used to generate the necessary intensive, large-scale mixing movement between hot gases and the mixed air to be mixed in in the form of a secondary flow, which, in contrast to the usual procedure, is independent of the mixed air jet.
  • the mixed air is now evenly fed to the hot gas through a number of small bores in the combustion chamber wall, that a supercritical blow-out rate is aimed at, which at the same time ensures effusion cooling. Due to the desired supercritical blow-out rate, the mixed air penetrates into the edge zones of the vortices induced by the vortex generators, is carried away from the wall by these vortices and accordingly mixes quickly with the hot gases. Since the vortex generators are directly exposed to the hot gases, the sufficient cooling that can be achieved with them is an essential prerequisite for such a mixing section.
  • the effusion cooling effect is mainly based on the internal convective cooling when the mixed air passes through the flow openings and on the possible formation of a cooling air film on the hot gas side. If the ratio between the momentum of the mixed air jet and that of the hot gas flow is small enough, the flow boundary layer on the hot gas side will not be penetrated by the mixed air and a cooling air film can form optimally. If this blowout rate exceeds a critical value, the mixed air jet penetrates into the hot gas flow without forming a cooling air film. With a suitable design, as the blow-out rate increases, the cooling effect inside the wall increases at the same time so that the overall cooling effect can be kept approximately constant.
  • the penetration depth of the Mixed air jet into the hot gas flow near the vortex generators must be kept low, at least an order of magnitude smaller than with the usual air inlet openings, since it only has to be so large that the mixed air penetrates the vortex, but the mixed air jet itself does not have to provide the necessary large-scale turbulence . Therefore, large diameters are not required and the mixed air can be supplied over a large area.
  • the proposed mixing section can also be adapted to different load conditions of the gas turbine. If the pressure drop available for the mixing is made variable, for example via an adjustable pre-throttle, the mixed air flow to be mixed in can also be controlled. If the blow-out rate changes from the supercritical to the subcritical range, the effusion cooling has a constant effect over a large load range despite the large variation in the mixed air flow. In this way, the air to be mixed in is supplied to the mixing process over a large area, thus increasing the overall mixing quality, and the wall of the mixing section is protected from excessive temperatures regardless of the mixing capacity.
  • variable mixing section can be used both in the usual diffusion and premixing combustion chambers and in combustion chamber concepts with staged combustion.
  • the combustion chamber here is an annular combustion chamber 100 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.
  • this combustion chamber can be the only combustion stage of a gas turbine or a combustion stage of a sequentially fired gas turbine.
  • the annular combustion chamber 100 according to FIG. 1 consists of a primary zone 1 in the flow direction, which is then followed by a mixing section 2, and this is followed by a secondary stage 3, which is preferably designed as an inflow to a turbine.
  • the burner and the fuel supply and the primary air supply are essentially placed at the beginning of the primary zone 1 and are symbolized by arrow 13 in the present FIG. 1.
  • the primary zone 1 is covered with a spaced concentric tube 11; between them flows a flow of cooling air 12 in the counterflow direction, which ensures convective cooling of the primary zone 1. This air can then pass through the burners, for example, after the passage has been completed.
  • the hot gases 4 from the primary zone 1 flow into the mixing section 2; the inner wall 6 and the outer wall 5 of this mixing section 2 are equipped with a series of vortex generators 200, which can be arranged differently in different circumferential directions of the walls mentioned.
  • the various forms, modes of action and arrangements of the vortex generators 200 are discussed in more detail below.
  • the mixing section 2 is encased by a chamber 10, into which a mixed air 8 flows through regulating elements 9 and is then distributed there through the various openings in the inner wall 6 and outer wall 5 and through the vortex generators 200, in order subsequently to to flow the mixing section 2.
  • the openings mentioned can be seen, for example, in FIGS. 8, 10, 12, 14 and 15; these figures will be explained in more detail below.
  • the mixed air 8 is in itself of a larger amount, for example up to 50% and more of the total mass flow. With such a quantity of mixed air, the blow-out rate into the mixing section 2 is supercritical, which is why a cooling film along the walls 5, 6 cannot develop per se.
  • Openings on all sides through the vortex generators 200 also provide adequate cooling of the latter against the hot gases 4.
  • the supercritical blow-out rate also ensures that the depth of penetration of the mixed air 8 into the hot gases 4 in the region of the vortex generators 200 is kept small can be. It only has to be large enough that the mixed air 8 penetrates into the eddies triggered by the vortex generators 200, but not that the inflowing mixed air 8 has to ensure large-scale turbulence. Therefore, the openings do not have a large cross-section, respectively. Diameter, wherein the introduction of the mixed air 8 can take place over a large area within the mixing section 2.
  • the introduction of the mixed air 8 into the mixing section 2 can be regulated depending on the load of the system.
  • the vertical connecting edge (cf. 4-7, item 216) of the vortex generators 200 also forms the transition from the mixing section 2 to the secondary stage 3, which results in a constriction of the mixing zone 2, which then leads to an immediate cross-sectional jump 14 at the beginning of the secondary stage 3 leads.
  • the variable distribution of the mass flows 4, 8 has the effect that, depending on the load condition of the system, the cooling effect of the mixed air 8 when it passes through the wall either through the heat transfer inside the Openings alone or through a combination with the cooling film.
  • the first case is a supercritical case with a high mass flow and high admission pressure
  • the second case is a subcritical case with a low mass flow and low admission pressure.
  • the mixing configuration thus formed is variable in the sense that the mixed air flow 8 may be heavily load-dependent without the material, in particular the vortex generators 200 and the walls 5, 6 overheating.
  • the design criterion regarding the injection geometry is accordingly a cooling effectiveness that is only weakly dependent on the mixed air flow 8 over a larger area.
  • Such a mixing section 2 designed in this way is used both in staged combustion and in burners, the aim here being to be able to drive with a constant fuel-air ratio despite a variable load.
  • FIG. 2 is a section of the sectional plane II-II of FIG. 1 and shows a configuration of vortex generators 200, which are fixed both on the outer wall 5 and on the inner wall 6. They are adjacent to one another in the circumferential direction, the flow of the hot gases 4 through the free space being given by the radial spacing of the opposite tips of the vortex generators 200 and by the gaps between the freely flowing surfaces.
  • the curved lines shown in this figure represent the vortices triggered by the vortex generators 200.
  • FIG. 3 largely corresponds to FIG. 2, in which case the vortex generators 200 are only fixed to the inner wall 6.
  • a vortex generator 200, 201, 202 essentially consists of three flowed around freely triangular faces. 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 at least on the already mentioned channel wall 6, 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 5, 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 transverse to the flow channel. Its longitudinal edges 212, 214 are flush with the longitudinal edges of the side surfaces 211 protruding into the flow channel , 213.
  • the roof surface 210 extends at an angle of 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 floor surface with which it rests 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 swirl number and the location of the vortex breakdown (vortex breakdown), if the latter is aimed for, the angle of attack e and the arrow angle ⁇ are determined by appropriate choice.
  • the vortex strength or the number of swirls is increased, and the location of the vortex bursting shifts upstream into the area of the vortex generator 200, 201, 202 itself.
  • these two angles ⁇ and ⁇ are due to the structural conditions and the Process specified by yourself.
  • These vortex generators only have to be adjusted in terms of length and height, as will be explained in more detail below under FIG. 7.
  • the connecting edge 216 of the two side surfaces 211, 213 forms the downstream side edge of the vortex generator 200.
  • the edge 215 of the roof surface 210 running transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • FIG. 5 shows a so-called half "vortex generator” based on a vortex generator according to FIG. 4.
  • 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 an overall swirl is imposed on the flow.
  • FIG. 6 differs from FIG. 4 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. 7 shows the basic geometry of a vortex generator 200 installed in the mixing section 2.
  • the height h of the connecting edge 216 is matched to the channel height H, or the height of the channel part which is assigned to the vortex generator, so that the generated one Vortex immediately downstream of the vortex generator 200 has already reached such a size that the full channel height H is thereby 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 and preferably used where it is a question of 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 mixed air 8 (cf. FIG. 1) has an amount which is up to 50% and more of the main flow 4. In the present case, this mixed air flow 8 is introduced upstream and downstream of the vortex generator and through the vortex generators themselves into the main flow 4, as can be seen particularly well from FIG. 1.
  • the vortex generators are placed flush with each other; Of course, these vortex generators can be distributed at a distance from one another over the circumference of the mixing section 2.
  • the vortex to be generated is ultimately decisive for the choice of the geometry, number and arrangement of the vortex generators.
  • FIGS. 8-15 show further vortex generators with different configurations with regard to the flow openings or bores for the inflow of the mixed air into the Mainstream.
  • these passages can also be used to introduce another or another medium, for example a fuel, into the mixing section.
  • channel wall bores 220 which are located downstream of the vortex generators, and further 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 to which the vortex generators are fixed.
  • the introduction of the mixed air flow through the wall bores 221 gives the generated vortices an additional impulse and cooling effect, which extends the life of the vortex generator.
  • the mixed air flow 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 flow 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 of the slot 222 is selected such that the mixed air, possibly a different medium, 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 mixed air flow as can be seen in FIG. 1, is introduced into the hollow interior of the vortex generators.
  • the intended mixing mechanism with respect to the main flow 4 and the eminently important cooling possibility for the vortex generators themselves are thus created without providing any further dispositives.
  • the mixed air flow can of course be based on a combination of the blowing options already described (Fig. 8-10) and on the basis of the further possibilities according to the following figures 11-15.
  • the arrowed flow openings in the various FIGS. 8-14 are only shown qualitatively, with which it is easily possible to provide the relevant or all surfaces of the vortex generator entirely with flow openings spaced apart from one another, as can be seen from FIG. 15 .
  • the mixed air flow is injected through bores 224, which occupy the roof surface 210, the inflow of the mixed air flow across the channel or. to edge 215 happens.
  • the vortex generator is cooled more externally than internally.
  • the emerging mixed air flow unfolds at a subcritical blowout rate when the roof surface 210 flows around a protective layer shielding it from the hot main flow 4, otherwise, at a supercritical blowout rate, the mixing effect occurs, as described under FIG. 1 has been.
  • the mixed air flow is injected via bores 225, which are staggered at least along the symmetry line 217 within the roof surface 210.
  • the channel walls 6 are particularly well protected from the hot main flow 4, since the mixed air flow is first introduced on the outer circumference of the vortex.
  • the mixed air flow is injected via bores 226 which are located at least in the longitudinal edges 212, 214 of the roof surface 210.
  • This solution ensures good cooling of the vortex generator, since the mixed air flow exits at its extremities and thus completely flushes around the inner walls of the element.
  • the mixed air flow is fed directly into the resulting vortex, which leads to a defined mixture within the main flow at a supercritical blow-out rate.
  • the mixed air flow is injected via 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. 8 ( Bores 221) and from Fig. 13 (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)
EP96810314A 1995-06-02 1996-05-17 Générateur de tourbillons pour chambre de combustion Expired - Lifetime EP0745809B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19520291 1995-06-02
DE19520291A DE19520291A1 (de) 1995-06-02 1995-06-02 Brennkammer

Publications (2)

Publication Number Publication Date
EP0745809A1 true EP0745809A1 (fr) 1996-12-04
EP0745809B1 EP0745809B1 (fr) 2008-11-12

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US (1) US5735126A (fr)
EP (1) EP0745809B1 (fr)
JP (1) JPH0914603A (fr)
CN (1) CN1244766C (fr)
DE (2) DE19520291A1 (fr)

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WO2000039503A1 (fr) 1998-12-23 2000-07-06 Alstom (Schweiz) Ag Bruleur pour generateur de chaleur
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
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JP2011102669A (ja) 2009-11-10 2011-05-26 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器及びガスタービン
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US11788724B1 (en) * 2022-09-02 2023-10-17 General Electric Company Acoustic damper for combustor
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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0455487A1 (fr) * 1990-05-03 1991-11-06 General Electric Company Chambre de combustion de turbine à gaz
EP0547808A1 (fr) * 1991-12-18 1993-06-23 General Electric Company Chambre de combustion avec alimentation en air étagée
EP0619456A1 (fr) * 1993-04-08 1994-10-12 ABB Management AG Système d'alimentation en carburant pour chambre de combustion
EP0694740A2 (fr) * 1994-07-25 1996-01-31 Abb Research Ltd. Chambre de combustion

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1203521A (fr) * 1958-02-04 1960-01-19 Snecma Dispositif de brûleur perfectionné destiné notamment aux chambres de combustion parcourues par un flux continu
GB1377636A (en) * 1972-11-20 1974-12-18 Secr Defence Combustors
JPS5260323A (en) * 1975-11-14 1977-05-18 Hitachi Ltd Gas-turbine combustor
US4292801A (en) * 1979-07-11 1981-10-06 General Electric Company Dual stage-dual mode low nox combustor
DE4034711C1 (en) * 1990-11-01 1992-02-27 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Secondary air feed control for gas turbine burner flame tube - has jacketed tube with spherical surface in region with air ports with throttle ring
FR2674317B1 (fr) * 1991-03-20 1993-05-28 Snecma Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
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.
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
DE4417538A1 (de) * 1994-05-19 1995-11-23 Abb Management Ag Brennkammer mit Selbstzündung

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0455487A1 (fr) * 1990-05-03 1991-11-06 General Electric Company Chambre de combustion de turbine à gaz
EP0547808A1 (fr) * 1991-12-18 1993-06-23 General Electric Company Chambre de combustion avec alimentation en air étagée
EP0619456A1 (fr) * 1993-04-08 1994-10-12 ABB Management AG Système d'alimentation en carburant pour chambre de combustion
EP0694740A2 (fr) * 1994-07-25 1996-01-31 Abb Research Ltd. Chambre de combustion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
KOEHLER J ET AL: "CALCULATION OF THE DISTURBANCE TO COMBUSTION CHAMBER FILM COOLING DUE TO AIR INJECTION THROUGH A ROW OF JETS", ZEITSCHRIFT FUR FLUGWISSENSCHAFTEN UND WELTRAUMFORSCHUNG, vol. 9, no. 1, 1 January 1985 (1985-01-01), pages 34 - 42, XP000573338 *

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0999367A1 (fr) 1998-11-06 2000-05-10 ABB Alstom Power (Schweiz) AG Conduit d'écoulement à discontinuité de section transversale
US6216644B1 (en) 1998-11-06 2001-04-17 Abb Alstrom Power (Schweiz) Ag Flow duct with cross-sectional step
WO2000039503A1 (fr) 1998-12-23 2000-07-06 Alstom (Schweiz) Ag Bruleur pour generateur de chaleur
US6702574B1 (en) 1998-12-23 2004-03-09 Alstom (Schweiz) Ag Burner for heat generator
EP1382379A2 (fr) * 2002-07-20 2004-01-21 ALSTOM (Switzerland) Ltd Générateur de tourbillons avec contrôle de fluide en aval
EP1382379A3 (fr) * 2002-07-20 2004-05-12 ALSTOM Technology 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
DE10250208A9 (de) * 2002-10-28 2004-12-23 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
CN101067497A (zh) * 2006-05-04 2007-11-07 通用电气公司 用于膨胀燃烧器内的初级火焰和次级火焰的方法和装置
EP1975506A1 (fr) * 2007-03-30 2008-10-01 Siemens Aktiengesellschaft Pré-chambre de combustion
WO2008119737A1 (fr) * 2007-03-30 2008-10-09 Siemens Aktiengesellschaft Préchambre de combustion
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
WO2015088687A1 (fr) * 2013-12-11 2015-06-18 Siemens Aktiengesellschaft Système de combustion d'une turbine à gaz

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JPH0914603A (ja) 1997-01-17
DE59611488D1 (de) 2008-12-24
US5735126A (en) 1998-04-07
CN1160150A (zh) 1997-09-24
EP0745809B1 (fr) 2008-11-12
CN1244766C (zh) 2006-03-08
DE19520291A1 (de) 1996-12-05

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