EP1182398B1 - Procédé pour accroítre la stabilité fluidique d'un brûleur de prémélange ainsi que brûleur de prémélange pour mettre en oeuvre le procédé - Google Patents
Procédé pour accroítre la stabilité fluidique d'un brûleur de prémélange ainsi que brûleur de prémélange pour mettre en oeuvre le procédé Download PDFInfo
- Publication number
- EP1182398B1 EP1182398B1 EP01120011A EP01120011A EP1182398B1 EP 1182398 B1 EP1182398 B1 EP 1182398B1 EP 01120011 A EP01120011 A EP 01120011A EP 01120011 A EP01120011 A EP 01120011A EP 1182398 B1 EP1182398 B1 EP 1182398B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- flow
- cavity
- section
- premix
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
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- 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
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
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- 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
- F23D11/402—Mixing chambers downstream of the nozzle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/74—Preventing flame lift-off
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2209/00—Safety arrangements
- F23D2209/20—Flame lift-off / stability
Definitions
- the invention relates to a method for fluid mechanical stabilization of a premix burner, in which a combustion air flow is introduced tangentially into a burner interior, mixed to form a coaxially oriented swirl flow with a injected gaseous and / or liquid fuel and induces a remindströmzone at a burner outlet, which during operation of the burner serves to stabilize the flame. Furthermore, the invention relates to a premix burner for carrying out the method.
- a preferred field of application of the invention is the operation of a gas turbine plant.
- EP 0 321 809 and EP 0 780 629 disclose premix burners of the type discussed herein known. Such burners, which are characterized by very low pollutant emissions, are widely used in combustion chambers of gas turbine plants Hot gas generation used.
- thermoacoustic oscillations often occur in the combustion chambers.
- resulting fluid mechanical instability waves lead to the formation of flow vortex, which strongly influence the entire combustion process and lead to unwanted periodic heat releases within the combustion chamber, which are associated with strong pressure fluctuations.
- the high pressure fluctuations are associated with high vibration amplitudes, which can lead to undesirable effects, such as a high mechanical load of the combustion chamber, increased NO x emissions by inhomogeneous combustion and even to extinguish the flame within the combustion chamber.
- Thermoacoustic oscillations are based at least in part on flow instabilities burner flow, which manifests itself in coherent flow structures, and which influence the mixing processes between air and fuel.
- burner flow which manifests itself in coherent flow structures, and which influence the mixing processes between air and fuel.
- conventional Combustion chambers become cooling air in the manner of a cooling air film over the combustion chamber walls directed.
- the cooling air film also has a sound-absorbing effect and contributes to the reduction of thermoacoustic vibrations.
- the cooling air flow significantly reduced in the combustion chamber and almost all of the air is passed through the burner.
- this also reduces the sound-absorbing effect at the same time Cooling air film, whereby the sound-absorbing effect is reduced and reinforces the problems associated with the unwanted vibrations occur.
- thermoacoustic vibration amplitudes has the disadvantage that the injection of fuel at the head stage can be accompanied by an increase in the emission of NO x .
- thermoacoustic vibrations have shown that such unwanted coherent structures arise in mixing operations. Of particular importance here are those between two mixing Currents forming shear layers that are within the coherent structures be formed. Further details can be found in the following publications: Oster & Wygnanski 1982, "The forced mixing layer between parallel 123, 91-130; Paschereit et al., 1995, “Experimental investigation of subharmonic resonance in an axisymmetric jet ", Journal of Fluid Mechanics, Vol. 283, 365-407).
- the invention is based on the object, a method for increasing the fluid mechanical To provide stability of a premix burner, which the undesirable eddies, posing as coherent pressure fluctuation structures training, efficient and suppressed without additional energy.
- the purpose necessary measures on a premix burner should have a low constructive Create effort and be cost effective in their realization.
- the Furthermore, the measures taken should be completely maintenance-free.
- the object is achieved by a method for increasing the fluid mechanical stability of a premix burner and by a premix burner of the type mentioned in the independent claims.
- the idea of the invention advantageously further features are the subject of the dependent claims.
- the method according to the invention is based on the basic idea of fluid mechanics Stabilization of a premix burner, in which at least one Combustion air flow is introduced tangentially into a burner cavity and forming a coaxial with the burner axis oriented swirl flow with a injected gaseous and / or liquid fuel mixed and at one Cross-section jump at the burner mouth induces a backflow zone, which during operation of the burner serves to stabilize the flame, the swirl flow within of the burner cavity towards the burner mouth at least increasingly radially deforming a peripheral portion and in a non-rotationally symmetric Flow cross-section to enter the combustion chamber, this deformation being at the expense of the free flow cross-section of the burner cavity is produced.
- a premix burner according to the invention is based on a premix burner for use in a heat generator, essentially consisting of a swirl generator with means for tangentially introducing a combustion air flow in a cavity of the swirl generator and means for introducing at least a gaseous and / or liquid fuel in the combustion air stream below Formation of a swirl flow with an axial component of motion towards the Burner mouth, at which the swirl flow inducing a backflow zone bursts.
- a generic burner based on at least two hollow, in Flow direction of the hot gases nested conically widening Partial bodies whose center axes are offset from one another are described in EP 0321809 described.
- Such types of burners also known as cone burners or double-cone burners, have at their burner outlet on a spoiler edge, the edge course of consists of two mutually offset semicircles whose closed edge course However, almost circular and thus approximately rotationally symmetrical to the burner axis is trained.
- Such influence on the flow geometry can by at least a section of the cavity wall take place, which wall section in a downstream end portion of the burner cavity has a lower pitch as in an upstream area.
- This at least one section leads to it opposite those wall sections at the same axis height, this feature do not possess, to a radial deviation from the circular shape in the direction of the Brenner axis.
- FIGS. 1a and 1b show in a highly schematized form the structure and mode of action of a premix burner, as it is the starting point of the invention presented here.
- the premix burner consists of two hollow conically widening part bodies (1) and (2), which are arranged axially parallel and offset from one another such that they form tangential gaps (3) in two mirror-inverted overlapping regions.
- two conically widening partial bodies (1) and (2) are shown by way of example in FIGS. 1a and 1b, other configurations are also conceivable. Thus, these burners are not limited to the arrangement of two partial bodies (1) and (2), nor is their conical configuration absolutely necessary. This is familiar to the expert.
- the resulting from the displacement of the longitudinal axes column (3) serve as inlet channels through which the burner air combustion air (5) flows tangentially into the burner cavity (6).
- injection openings (7) there are injection openings (7), through which a preferably gaseous fuel is injected into the passing combustion air (5).
- the fuel injection preferably takes place within the gap (3) immediately before entry into the burner cavity (6).
- a central nozzle (8) is provided for atomizing a liquid fuel whose capacity and mode of operation are governed by the burner parameters.
- the premix burner On the combustion chamber side, the premix burner has a front plate (10) which acts as an anchorage of the part bodies (1) and (2) and has a number of bores (11) for introducing air into the combustion chamber (12).
- the fuel / air mixture passing through the burner cavity (6) in a swirl flow (9) reaches the optimum fuel concentration across the cross section at the downstream end of the premix line (13) at the burner mouth (14).
- the swirl flow (9) bursts to form a backflow zone (15) with an effect stabilizing against the flame front (17) acting there.
- This aerodynamic flame stabilization acts as a kind of flame holder.
- the dreaded failure of mechanical flame holders due to overheating with possible subsequent serious damage to machine sets is thus excluded.
- the flame loses no heat except on cold walls due to radiation. This also contributes to the uniformity of the flame temperature and thus to low pollutant emissions and good combustion stability.
- measures are now provided to increasingly radially deform the swirl flow (9) within the premix section (13).
- this deformation should be symmetrical. This is not mandatory. It is an essential feature to achieve this deformation at the expense of the free flow cross-section (18).
- the wall (21) of the cavity (6) has, in a downstream region (20), at least one section (22) which has a smaller pitch relative to an upstream region (19) relative to the burner axis (4).
- the approximately circular contour (21) of the burner cavity (6) viewed over the cross section, has a deviation from the circumference of the cavity contour (21) in the direction of the central axis (4), ie the cavity (6) constricts Sections (22), as shown in Fig 2a-2d in longitudinal section schematically reproduced. It has proven to be advantageous in this context, to accompany the deformation of the flow simultaneously with an acceleration of the flow. This measure has a particularly favorable effect on the stability of the burner.
- the cross-sectional shape deviating from the rotational symmetry of the flow (9) emerging from the burner has a disruptive effect on the formation of coherent vortex structures and thus ultimately inhibits the formation of thermoacoustic oscillations.
- FIGS. 2a-2d are intended to explain the concept of the invention on the basis of highly schematic representations.
- FIGS. 2b-2d symbolize the concept of the invention, which for the purpose of deforming the airfoil, the wall (21) of the burner cavity (6) in at least one peripheral portion (22) at the expense of the free flow cross-section (18) in the direction of the burner axis (4) to angle. This can be done symmetrically or asymmetrically by at least one of the flow cross-section constricting portion (22).
- FIGS. 3 to 7 show embodiments of burners designed according to the invention.
- FIG 3 shows a preferred variant of the invention, according to which the burner mouth (14) has a polygonal outlet contour (16).
- the conically widening contour (23) of the burner cavity (6) is broken off in a downstream end region (20) and has a smaller pitch than the preceding region (19) in relation to FIG Longitudinal axis (4) continued.
- the term reduced slope should also include a profile parallel to the longitudinal axis (4) or a convergent profile, as shown in FIGS. To realize this suggestion, a variety of measures are available to the person skilled in the art.
- the circle segments from the free flow cross-section (18) of the burner cavity (6) cut out For each partial body (1) or (2), preferably one to four such plates (28) are welded onto the inner wall (21).
- the burner is formed in an upstream region (19) in a manner known per se from two interleaved partial bodies (1) and (2) of substantially circular cross-section.
- a convex course is particularly advantageous in the case of the arrangement of a small number or only one or two such sections (22).
- Another embodiment is not to provide the burner cavity (6) in its upstream region (19) with a circular cross-section, but to equip the burner with a continuous non-rotationally symmetric contoured cavity (6).
- This embodiment is particularly suitable for polygonal contours (23) of the cavity cross section (18).
- FIGS. 5 and 6 show a premix burner, consisting of a swirl generator (13) for a combustion air stream (5) and means for injecting at least one fuel (7) and / or (8), wherein downstream of the swirl generator (13) has a mixing section (25) is arranged.
- the mixing section (25) bounding housing (26) can be arranged in an even circumferential distribution pointed to the longitudinal axis (4) extending inlet openings (27) for injecting an additional amount of combustion air.
- the exit port (16) occupies a polygonal cross-sectional shape composed of a plurality of rectilinear portions (22). Promising exit contours (16) in the form of a regular or irregular polygon ( Figure 5).
- the individual rectilinear sections (22) of the outlet edge (27) span the outlet opening (16) of the burner.
- FIG. 7 shows a variant embodiment with a cylindrical or convergent nozzle section (24) at the downstream burner end.
- these downstream nozzles (24) serve primarily to accelerate the flow at the burner outlet and thus stabilize the return flow zone (15).
- this desirable acceleration is achieved by increasing and decreasing the cross-sectional area such that this nozzle portion (24) is narrowed in the direction of flow from a substantially circular cross-sectional shape to another cross-sectional shape, such as a regular or irregular polygon or one oval.
- FIG. 8 shows a diagram showing the combustion power along the abscissa of the burner according to FIG. 3 and along the ordinate a scaling that allows the formation of thermoacoustic vibrations as Result in coherent structures within the flow stream in the burner, quantified.
- thermoacoustic vibrations in the 100 Hz range. Comparing a burner with conventional burner outlet according to the embodiment in Figure 1 (see polyline with squares interspersed) with an inventive trained burner outlet according to embodiment in Figure 3 (see figure interspersed with circles), it is clear that in the latter case a considerable lower proportion of thermoacoustic vibrations arises.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Claims (20)
- Procédé de stabilisation fluidique d'un brûleur de prémélange dans lequel au moins un courant d'air comburant est introduit tangentiellement dans une cavité du brûleur et se mélange avec un combustible gazeux et/ou liquide pulvérisé en formant un écoulement tourbillonnaire orienté coaxialement à l'axe du brûleur, et induit une zone de reflux au niveau d'un saut de section transversale à l'embouchure du brûleur, laquelle sert à stabiliser la flamme au cours du fonctionnement du brûleur, caractérisé en ce que l'écoulement tourbillonnaire est déformé de manière croissante à l'intérieur de la cavité du brûleur dans la direction de l'embouchure du brûleur et pénètre dans la chambre de combustion avec une section transversale d'écoulement n'ayant pas une symétrie de révolution, cette déformation étant produite au détriment de la section transversale d'écoulement libre.
- Procédé selon la revendication 1, caractérisé en ce que la déformation de l'écoulement tourbillonnaire s'accompagne d'une augmentation de la vitesse d'écoulement.
- Procédé selon la revendication 2, caractérisé en ce que la déformation s'accompagne d'une réduction de la section transversale d'écoulement libre de la cavité du brûleur.
- Procédé selon la revendication 1, caractérisé en ce que la déformation est obtenue de telle manière qu'au moins une portion périphérique de la paroi de la cavité présente dans une région aval de la cavité du brûleur une pente plus faible que dans une région amont.
- Procédé selon la revendication 1, caractérisé en ce que le profil d'écoulement déformé est symétrique par rapport à au moins un axe.
- Procédé selon la revendication 4, caractérisé en ce que le profil d'écoulement prend le contour d'un polygone.
- Procédé selon la revendication 1, caractérisé en ce qu'il est utilisé pour le fonctionnement de brûleurs de prémélanges pauvres d'une installation de turbine à gaz.
- Brûleur de prémélange pour l'utilisation dans un générateur de chaleur, se composant essentiellement d'un générateur de tourbillon (13) ayant des moyens (3) pour l'introduction tangentielle d'un courant d'air comburant (5) dans une cavité (6) du générateur de tourbillon (13) ainsi que des moyens (7 ; 8) pour l'introduction d'au moins un combustible gazeux et/ou liquide dans le courant d'air comburant (5) en formant un écoulement tourbillonnaire (9) avec une composante de déplacement axiale vers l'embouchure du brûleur (14), caractérisé en ce que le contour de la cavité (21) se prolonge dans la direction de l'écoulement d'une forme en section transversale ayant substantiellement une symétrie de révolution à une forme en section transversale n'ayant pas une symétrie de révolution par le fait qu'au moins une portion (22) de la paroi de la cavité (21), vu sur la périphérie, prend, dans une région d'extrémité aval (20), une pente plus faible que dans une région amont (19) par rapport à l'axe longitudinal du brûleur (4) au détriment de la section transversale libre.
- Brûleur de prémélange selon la revendication 8, comprenant au moins deux corps partiels (1) et (2) creux, s'élargissant coniquement, emboítés l'un dans l'autre coaxialement à l'axe longitudinal (4), dont les axes médians s'étendent de manière décalée l'un par rapport à l'autre et dont les parois (21) forment dans une région de chevauchement des canaux d'entrée tangentiels (3) pour l'air comburant (5), et au moins un injecteur de carburant (8) à l'intérieur de la cavité (6) formée par les corps partiels (1) et (2), caractérisé en ce que la paroi (21) limitant l'écoulement, d'au moins l'un des corps partiels (1) ou (2), possède, dans une région d'extrémité aval (20) au moins une portion périphérique (22) qui présente, par rapport à une région amont (19), une pente plus faible par rapport à l'axe longitudinal du brûleur (4).
- Brûleur de prémélange selon la revendication 8 ou 9, caractérisé en ce qu'il existe une pluralité, de préférence de deux à huit de ces portions (22) réparties sur la périphérie.
- Brûleur de prémélange selon la revendication 10, caractérisé en ce que le brûleur présente, dans une région d'extrémité (20) incluant l'embouchure du brûleur (14), un contour polygonal.
- Brûleur de prémélange selon la revendication 11, caractérisé en ce que le brûleur présente le contour d'un polygone régulier.
- Brûleur de prémélange selon la revendication 11, caractérisé en ce que le brûleur présente le contour d'un polygone irrégulier.
- Brûleur de prémélange selon la revendication 9, caractérisé en ce qu'au moins l'un des corps partiels (1) ou (2) délimite une section transversale de sortie (16) convexe, s'écartant d'un profil rond circulaire.
- Brûleur de prémélange selon la revendication 14, caractérisé par une section transversale de sortie (16) au moins approximativement symétrique.
- Brûleur de prémélange selon la revendication 8, caractérisé en ce que la paroi (21) délimitant l'écoulement, de la cavité du brûleur (6), s'étend d'une pente à l'autre de manière continue entre la région amont (19) et la région d'extrémité aval (20) ou bien suivant un ou plusieurs échelons.
- Brûleur de prémélange selon la revendication 8, caractérisé en ce que la région d'extrémité aval (20) comprend approximativement le dernier tiers de la longueur de la cavité du brûleur (6).
- Brûleur de prémélange selon la revendication 8, caractérisé en ce que dans une région aval (20) à l'intérieur de la cavité du brûleur (6) sur la paroi (21), sont soudées ou fixées d'une autre manière appropriée, des plaques (28) délimitant la section transversale d'écoulement libre (18).
- Brûleur de prémélange selon la revendication 8, comprenant un générateur de tourbillon (13) ayant des moyens (3) pour l'introduction tangentielle d'un courant d'air comburant (5) dans une cavité (6) du générateur de tourbillon (13) ainsi que des moyens (7 ; 8) pour l'introduction d'au moins un combustible gazeux et/ou liquide dans le courant d'air comburant (5) en formant un écoulement tourbillonnaire (9) avec une composante de déplacement axiale vers l'embouchure du brûleur (14) et un injecteur de brûleur (24) à l'extrémité du côté de la chambre de combustion, caractérisé en ce que la section transversale d'écoulement libre (33) de l'injecteur (24) diminue dans la direction de l'écoulement en passant simultanément d'une forme de section transversale essentiellement à symétrie de révolution à une forme n'ayant pas une symétrie de révolution, par le fait qu'au moins une portion périphérique (22) de la paroi de l'injecteur (34) prend, dans une région aval (36), une distance plus faible par rapport à l'axe longitudinal de l'injecteur (4) que dans une région amont (35).
- Brûleur de prémélange, comprenant au moins deux corps partiels (1) et (2) creux, s'élargissant coniquement, emboítés l'un dans l'autre coaxialement à l'axe longitudinal (4), dont les axes médians s'étendent de manière décalée l'un par rapport à l'autre et dont les parois (21) forment dans une région de chevauchement des canaux d'entrée tangentiels (3) pour l'air comburant (5), et au moins un injecteur de carburant (8) à l'intérieur de la cavité (6) formée par les corps partiels (1) et (2), comprenant en outre une section de mélange (25) en aval du générateur de tourbillon (13) formé par les corps partiels (1) et (2), laquelle section de mélange (25) présente, à l'intérieur d'une première région de départ, des canaux de transition s'étendant dans la direction de l'écoulement pour l'écoulement tourbillonnaire (9) formé dans la cavité (6), et débouche dans la chambre de combustion (12) au niveau d'un bord de rupture (27), caractérisé en ce que la section transversale d'écoulement libre (29) de la section de mélange (25) diminue dans la direction de l'écoulement en passant simultanément d'une forme de section transversale essentiellement à symétrie de révolution à une forme n'ayant pas une symétrie de révolution, par le fait qu'au moins une portion périphérique (22) de la paroi (30) délimitant la section de mélange prend, dans une région aval (32), une distance plus faible par rapport à l'axe longitudinal de l'injecteur (4) que dans une région amont (31).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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DE10040869 | 2000-08-21 | ||
DE10040869A DE10040869A1 (de) | 2000-08-21 | 2000-08-21 | Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine |
Publications (2)
Publication Number | Publication Date |
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EP1182398A1 EP1182398A1 (fr) | 2002-02-27 |
EP1182398B1 true EP1182398B1 (fr) | 2005-11-16 |
Family
ID=7653185
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01120011A Expired - Lifetime EP1182398B1 (fr) | 2000-08-21 | 2001-08-20 | Procédé pour accroítre la stabilité fluidique d'un brûleur de prémélange ainsi que brûleur de prémélange pour mettre en oeuvre le procédé |
Country Status (4)
Country | Link |
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US (1) | US6599121B2 (fr) |
EP (1) | EP1182398B1 (fr) |
JP (1) | JP4819260B2 (fr) |
DE (2) | DE10040869A1 (fr) |
Families Citing this family (31)
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DE10049203A1 (de) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Verfahren zur Brennstoffeinleitung in einen Vormischbrenner |
GB2397643A (en) * | 2002-12-04 | 2004-07-28 | Alstom | A combustion chamber burner including a corrugated burner outlet |
DE10257275A1 (de) * | 2002-12-07 | 2004-06-24 | Alstom Technology Ltd | Verfahren und Vorrichtung zur Beeinflussung thermoakustischer Schwingungen in Verbrennungssystemen |
CA2555481A1 (fr) * | 2004-02-12 | 2005-08-25 | Alstom Technology Ltd | Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion |
WO2005095863A1 (fr) * | 2004-03-31 | 2005-10-13 | Alstom Technology Ltd | Brûleur |
WO2006069861A1 (fr) * | 2004-12-23 | 2006-07-06 | Alstom Technology Ltd | Bruleur de premelange dote d'un parcours de melange |
US7421843B2 (en) * | 2005-01-15 | 2008-09-09 | Siemens Power Generation, Inc. | Catalytic combustor having fuel flow control responsive to measured combustion parameters |
EP1852657A4 (fr) * | 2005-02-25 | 2012-02-29 | Ihi Corp | Soupape d injection de carburant, chambre de combustion utilisant ladite soupape, et procede d injection de carburant pour ladite soupape |
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KR100715027B1 (ko) * | 2005-12-10 | 2007-05-09 | 재단법인서울대학교산학협력재단 | 연소기 |
EP2041494B8 (fr) * | 2005-12-14 | 2015-05-27 | Industrial Turbine Company (UK) Limited | Injecteurs de prémélange de turbine à gaz |
CH699322A1 (de) * | 2008-08-14 | 2010-02-15 | Alstom Technology Ltd | Verfahren zum einstellen eines helmholtz-resonators sowie helmholtz-resonator zur durchführung des verfahrens. |
US20100192577A1 (en) * | 2009-02-02 | 2010-08-05 | General Electric Company | System and method for reducing combustion dynamics in a turbomachine |
EP2348256A1 (fr) * | 2010-01-26 | 2011-07-27 | Alstom Technology Ltd | Procédé de fonctionnement d'une turbine à gaz et turbine à gaz |
US8572981B2 (en) | 2010-11-08 | 2013-11-05 | General Electric Company | Self-oscillating fuel injection jets |
US8943832B2 (en) * | 2011-10-26 | 2015-02-03 | General Electric Company | Fuel nozzle assembly for use in turbine engines and methods of assembling same |
US8640820B2 (en) * | 2012-01-11 | 2014-02-04 | Polytechnic Institute Of New York University | High-speed jet noise reduction via fluidic injection |
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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 |
EP2700879B1 (fr) * | 2012-08-24 | 2019-03-27 | Ansaldo Energia Switzerland AG | Procédé pour mélanger un air de dilution dans un système de combustion séquentielle d'une turbine à gaz, et système de combustion séquentielle pour une turbine à gaz comprenant un injecteur d'air de dilution |
EP2912381B1 (fr) * | 2012-10-24 | 2018-06-13 | Ansaldo Energia Switzerland AG | Combustion séquentielle avec mélangeur de gaz d'appoint |
DE102014205201A1 (de) * | 2014-03-20 | 2015-09-24 | Kba-Metalprint Gmbh | Vorrichtung zur thermischen Nachverbrennung von Abluft |
DE102014205198A1 (de) * | 2014-03-20 | 2015-09-24 | Kba-Metalprint Gmbh | Brenner und Vorrichtung zur thermischen Nachverbrennung von Abluft |
DE102014205200B3 (de) | 2014-03-20 | 2015-06-11 | Kba-Metalprint Gmbh | Vorrichtung zur thermischen Nachverbrennung von Abluft |
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JP6934359B2 (ja) * | 2017-08-21 | 2021-09-15 | 三菱パワー株式会社 | 燃焼器及びその燃焼器を備えるガスタービン |
US11098894B2 (en) * | 2018-07-11 | 2021-08-24 | Praxair Technology, Inc. | Multifunctional fluidic burner |
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EP4078032A1 (fr) | 2020-03-31 | 2022-10-26 | Siemens Energy Global GmbH & Co. KG | Composant de brûleur d'un brûleur, et brûleur d'une turbine à gaz présentant un composant de brûleur de ce type |
CN112923364A (zh) * | 2021-04-21 | 2021-06-08 | 苏州万硕联信息技术有限公司 | 一种燃烧器 |
CN113685272B (zh) * | 2021-10-26 | 2021-12-24 | 中国航发四川燃气涡轮研究院 | 一种大尺寸薄壁非对称对开的圆转方机匣 |
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GB2175684B (en) * | 1985-04-26 | 1989-12-28 | Nippon Kokan Kk | Burner |
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EP0985876A1 (fr) * | 1998-09-10 | 2000-03-15 | Abb Research Ltd. | Brûleur |
-
2000
- 2000-08-21 DE DE10040869A patent/DE10040869A1/de not_active Withdrawn
-
2001
- 2001-08-20 US US09/932,094 patent/US6599121B2/en not_active Expired - Lifetime
- 2001-08-20 EP EP01120011A patent/EP1182398B1/fr not_active Expired - Lifetime
- 2001-08-20 DE DE50108063T patent/DE50108063D1/de not_active Expired - Lifetime
- 2001-08-21 JP JP2001250830A patent/JP4819260B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US6599121B2 (en) | 2003-07-29 |
DE10040869A1 (de) | 2002-03-07 |
DE50108063D1 (de) | 2005-12-22 |
JP4819260B2 (ja) | 2011-11-24 |
US20020026796A1 (en) | 2002-03-07 |
JP2002130676A (ja) | 2002-05-09 |
EP1182398A1 (fr) | 2002-02-27 |
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