EP1706672B1 - Brûleur à prémélange et procédé permettant de faire fonctionner une chambre de combustion - Google Patents

Brûleur à prémélange et procédé permettant de faire fonctionner une chambre de combustion Download PDF

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Publication number
EP1706672B1
EP1706672B1 EP05701493A EP05701493A EP1706672B1 EP 1706672 B1 EP1706672 B1 EP 1706672B1 EP 05701493 A EP05701493 A EP 05701493A EP 05701493 A EP05701493 A EP 05701493A EP 1706672 B1 EP1706672 B1 EP 1706672B1
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EP
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Prior art keywords
flow
swirl
contour
burner
axis
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Not-in-force
Application number
EP05701493A
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German (de)
English (en)
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EP1706672A1 (fr
Inventor
Dr. Peter Flohr
Prof. Dr. Christian Oliver PASCHEREIT
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General Electric Technology GmbH
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Alstom Technology AG
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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
    • 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
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability

Definitions

  • the invention relates to a premix burner and a method for operating a combustion chamber with a liquid and / or gaseous fuel with a swirl generator for a combustion supply air to form a swirl flow and means for injecting fuel into the swirl flow, wherein the swirl generator indirectly via a mixing zone or directly adjacent to the combustion chamber in each case via a burner outlet, wherein at the burner outlet an unsteady in the flow direction of the swirl flow cross-sectional enlargement is provided, bursts through the swirl flow to form a return flow zone.
  • Premix burners of the aforementioned type are known from a variety of prepublished publications, such as. From the EP A1 0 210 462 as well as the EP B1 0 321 809 , to name just a few.
  • Premix burners of this type is the general principle of action, within a mostly designed as a conical swirl generator, which provides at least two with corresponding mutual overlap Operakegelschalen to produce a consisting of a fuel-air mixture swirl flow, which within a is brought in the flow direction of the premix burner combustion chamber to form a spatially stable as possible premix flame for ignition.
  • the spatial position of the premix flame is determined by the aerodynamic behavior of the swirl flow whose swirl increases with increasing propagation along the burner axis, thus becomes unstable and ultimately bursts through an unsteady cross-sectional transition between the burner and combustion chamber in an annular swirling flow to form a return flow in the front area, the premix flame forms
  • FIG. 2 shown in a schematic manner in the form of a longitudinal sectional view and has a conical swirl generator 1, whose two interposed Operakegelschalen each include two air inlet slots 2.
  • the swirl generator 1 opens at the burner outlet 3 via an unsteady cross-sectional widening directly into the combustion chamber 4.
  • a swirl flow is generated, which propagates in the axial flow direction with increasing swirl about the axial direction of the swirl generator. Due to the increasing swirl along the axial flow direction, the instability of the swirling flow increases and turns into an annular swirling flow with backflow.
  • the premix flame 7 forms, which stabilizes at the front region of the inner backflow zone 5.
  • premix burner described above is used to generate hot gases for driving a gas turbine plant, then for reasons of optimizing the efficiency of the gas turbine plant, it is necessary to keep the pressure loss across the burner as low as possible. Since swirl number and pressure loss are in direct proportionality to each other, the lowest possible swirl number within the swirl flow is desired, which should be just chosen so large that forms an inner backflow zone.
  • the front stagnation point 6 of the backflow zone 5 it is desirable to keep the front stagnation point 6 of the backflow zone 5 as aerodynamically stable as possible in order to prevent the premix flame front anchored to the front stagnation point 6 from causing strong thermoacoustic instabilities due to strong variation in the flame position, which not only has a lasting effect on the efficiency of a gas turbine plant but also cause significant stress on almost all components of the gas turbine plant which come into direct contact with the hot gases, which ultimately reduces the overall service life of the plant.
  • the desire for the highest possible aerodynamic stability of the front flame front within the backflow zone contradicts the efficiency-induced swirl reduction, which leads to smaller swirl gradients in the burner, especially at the location of the front stagnation point 6.
  • a smaller swirl gradient implies a greater deflection of the stagnation point in Direction of flow in case of possible interference and supports the above-described formation of thermoacoustic instabilities.
  • the invention has the object of developing a premix burner according to the features of the preamble of claim 1 such that on the one hand the aerodynamic stability of the inner remindströmzone should be increased in particular in the region of the front stagnation point, without having to take a significant additional burner pressure loss in purchasing. Furthermore, it is appropriate to provide a corresponding method for operating a combustion chamber, which is intended both to avoid the occurrence of thermoacoustic vibrations, and the effort to achieve the lowest possible burner pressure loss.
  • the premix burner according to the invention is based on the idea that the aerodynamic stability of the free inner backflow zone can be increased by locally increasing the swirl gradient of the swirl flow upstream of the forming backflow zone in the flow direction. Due to the merely local enlargement of the swirl gradient, ie along the axially propagating swirl flow within the premix burner, it is necessary to raise the swirl number in the axial flow direction spatially limited from an initial swirl number to a larger swirl number and then immediately lower it to the output swirl number or one compared to this smaller swirl number. It turns out that with the measure according to the invention, the overall burner pressure loss is insignificant is increased, resulting in no or very little impact on the overall efficiency of a gas turbine.
  • a premix burner with the features of the preamble of claim 1 is characterized in that upstream of the burner outlet, a contour that locally locally tapers the flow cross section of the swirl generator or, if present, the mixing zone in the flow direction is provided.
  • the flow cross-section locally tapered contour is arranged in the flow direction of a first, the flow cross-section steadily decreasing gate section, which merges continuously into a second gate section with a smallest flow cross-section, in which in the flow direction third, the flow cross section again steadily increasing the gate section connects.
  • the premix burner is a double-cone burner whose swirl generator consists essentially of two sub-cone shells, and no further mixing tube is provided between the double-cone burner and the combustion chamber, so that the swirl generator with its burner outlet directly into the combustion chamber via an unsteady cross-sectional widening opens
  • the provision of the invention which can be added as an additional form at a suitable axial location along the inner peripheral edge of both Operakegelschalen addition, whereby the possibility of Retrovistierley is given or the shaping is already integrally incorporated into the innwandige side of both Operakegelschalen for one elliptical cross-step shaping at the location of the narrowest or smallest flow cross section caused by the contour.
  • the inventive measure is also applicable to Vormischbrennersystemen whose swirl generator are assembled from more than two Operakegelschalen or provide a mixing tube between the swirl generator and combustion chamber as an additional mixing zone.
  • the flow cross-section tapering contour in the inner wall region of the mixing tube is provided near the burner outlet at the transition to the combustion chamber.
  • the inventive concept of the local flow cross-sectional tapering for the purpose of aerodynamic stabilization of the forming Ragströmzone within a premix burner, which is preferably used to operate a combustion chamber, which is used for firing a gas turbine plant, is based on the procedural idea, aerodynamic conditions at the location of the foremost stagnation point of remindströmzone to create, which prevent an axial emigration of the stagnation point.
  • the swirl flow oriented in the axial flow direction is determined by the contour-related nozzle effect accelerated within the vortex burner, for example within the swirl generator axially before the foremost stagnation point of scrubströmzone and also delayed in the flow direction before the stagnation point of mulchströmzone such that at the axial location of the stagnation point as large a speed gradient prevails with flow direction reversal.
  • This can be achieved by means of a convergent and divergent flow guidance that is specifically located in front of the location of the stagnation point. Further details can be found in the description of the embodiments in the further.
  • FIG. 1 shows a schematic section of a longitudinal section through a swirl generator of a double cone premix burner with a burner wall 8 with the burner axis A includes a half cone angle ⁇ .
  • a contour 9 which narrows the axial flow cross-section is provided on the inner wall of the burner wall 8.
  • the contour 9 reduces the flow cross-section along the burner axis A within a local area 10 such that the shape and size of the burner outlet 3 are not impaired by the contour 9.
  • the contour 9 has a first gate section 91, through which the flow cross section is steadily reduced.
  • a second gate section 92 which predetermines the smallest flow cross section.
  • the second gate section 92 is formed only point or linear.
  • a third link portion 93 through which the flow cross-section is widened again, preferably to a level which is predetermined by the burner wall 8 on the outlet side.
  • the contour 9 tapering in the flow cross-section runs in the circumferential direction to both partial cone shells annularly closed, so that through the interaction of the respective contours 9 attached to both partial cone shells, a flow slot is formed which corresponds to that of a Venturi nozzle.
  • burner axis and center axis of the respective cone shells
  • each individual sub-cone shell has a sub-conical central axis assigned to it, in short the central axis of the respective sub-cone shell. Due to the spatial arrangement of the subcone shells these corresponding central axes do not coincide. However, for the above design parameter requirements, it is necessary to raise to the corresponding center axes of the subcone cups.
  • FIG. 2 On the description of FIG. 2 has already been dealt with in detail in the introduction, so that a further description is omitted here.
  • FIG. 3 shows a schematic cross-section through a double-cone burner in the region of the contour-related narrowest flow cross-section 92.
  • Both partial cone shells 10, 11 each have their respective central axes M11, M 12 and are interlocked so that they include two opposing tangential air inlet slots 2 together.
  • Due to the contours 9, the entire flow cross-section is narrowed by the swirl generator in the manner of an ellipse shape (dashed line).
  • Such an elliptical flow cross section advantageously has aerodynamically stabilizing effects on the burner behavior over a wide operating range.
  • the contours 9 are thinned in accordance with aerodynamics accordingly in these areas, so as not to reduce the Schlüzweite ultimately.
  • FIG. 4 is a diagram for illustrating the axial velocity profile by the premix burner or swirl generator shown.
  • the x-axis corresponds to the burner axis, the y-axis to the flow direction oriented in the axial flow direction u of the burner flow.
  • the flow cross-section locally tapered contour 9 increases the axial flow velocity within the premix burner, is slowed down due to increasing flow instability and it is not least due to the unsteady cross-sectional widening at the burner outlet a local flow reversal (see location of the stagnation point 6), whereby the above-mentioned backflow zone (5) is formed.
  • FIG. 5 shows a diagram representation along the x-axis of the flame temperature and along the y-axis, the strength of pressure fluctuations in a normalized representation is indicated.
  • the polyline with the square markings corresponds to the operation of a premix burner with contouring according to the invention, the count interspersed with the diamonds corresponds to a conventional premix burner. It is very clear that, especially at low flame temperatures, much lower pressure fluctuations occur in the premix burner designed according to the invention than in a conventional one.
  • FIG. 6 a diagram is shown along the x-axis and along the y-axis of the nitrogen oxide concentration is plotted in a normalized representation.
  • Both the premix burner with contouring designed according to the invention (see line with rectangles) as well as a conventional premix burner (see line with diamonds) run largely parallel at a low level.

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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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)

Claims (11)

  1. Brûleur à prémélange pour faire fonctionner une chambre de combustion (4) avec un combustible liquide et/ou gazeux comprenant un générateur de tourbillon (1) pour un flux d'air comburant afin de produire un écoulement tourbillonnaire, et comprenant aussi des moyens pour injecter du combustible dans l'écoulement tourbillonnaire, le générateur de tourbillon (1) étant adjacent à la chambre de combustion (4), directement ou indirectement par le biais d'une zone de mélange, et à chaque fois par le biais d'une sortie du brûleur (3), un élargissement de section transversale étant prévu au niveau de la sortie du brûleur (3), de manière désaxé dans la direction d'écoulement de l'écoulement tourbillonnaire, à travers lequel l'écoulement tourbillonnaire éclate en formant une zone de reflux (5), le générateur de tourbillon (1) présentant au moins deux coques coniques partielles (11, 12) se complétant pour former un corps, lesquelles incluent ensemble un espace tourbillonnaire en forme de cône avec un angle de conicité 2γ ainsi que des fentes d'entrée d'air (2) tangentielles dans la direction longitudinale du cône, chaque coque conique partielle (11, 12) pouvant être associée à chaque fois à des axes médians respectifs (M11, M12), qui s'étendent de manière séparée physiquement l'un de l'autre, caractérisé en ce qu'en amont de la sortie du brûleur (3), on prévoit un contour (9) réduisant localement dans la direction de l'écoulement la section transversale d'écoulement du générateur de tourbillon (1) ou de la zone de mélange, le contour étant disposé dans la région du front avant de la zone de reflux dans la direction de l'écoulement et présentant, dans la direction d'écoulement, une première portion de coulisse (91) réduisant constamment la section transversale d'écoulement, une deuxième portion de coulisse (92) avec une section transversale d'écoulement minimale ainsi qu'une troisième portion de coulisse (93) augmentant constamment la section transversale d'écoulement et se raccordant dans la direction de l'écoulement à la deuxième portion de coulisse.
  2. Brûleur à prémélange selon la revendication 1,
    caractérisé en ce que le contour (9) est prévu sur le bord périphérique interne du générateur de tourbillon (1) ou de la zone de mélange.
  3. Brûleur à prémélange selon la revendication 1 ou 2,
    caractérisé en ce que le contour (9) inclut un canal d'écoulement, qui est réalisé à la façon d'un tube venturi.
  4. Brûleur à prémélange selon l'une quelconque des revendications 1 à 3,
    caractérisé en ce que la troisième portion de coulisse (93) possède une position axiale à l'intérieur du brûleur à prémélange qui est située dans la région du front (6) avant, dans la direction de l'écoulement, de la zone de reflux (5) qui se forme.
  5. Brûleur à prémélange selon l'une quelconque des revendications 1 à 4,
    caractérisé en ce que le générateur de tourbillon (1) est directement adjacent à la chambre de combustion (4) par le biais de la sortie de brûleur (3) et le contour (9) réduisant localement la section transversale d'écoulement du générateur de tourbillon (1) peut être décrit par les conditions géométriques suivantes : 0 , 5 ≤ R ⁢ 1 x / RB x ≤ 1
    Figure imgb0010
     0 , 5 ≤ R ⁢ 2 x / RB x ≤ 2
    Figure imgb0011
     et y < α < 40 ⁢ °
    Figure imgb0012
     avec :
    x : coordonnée de position le long de l'axe médian d'une coque conique partielle
    R1: distance radiale entre l'axe médian d'une coque conique partielle et la surface du contour au lieu x le long de l'axe médian
    RB : distance radiale entre l'axe médian d'une coque conique partielle et la surface de la coque conique partielle d'origine au lieu x le long de l'axe médian
    R2 : surélévation du contour mesurée depuis la surface de la coque conique partielle au lieu x le long de l'axe médian
    α : angle entre une surface tangentielle au contour et l'axe médian de la coque conique partielle au lieu x le long de l'axe médian
    γ : demi-angle de conicité.
  6. Brûleur à prémélange selon l'une quelconque des revendications 1 à 5,
    caractérisé en ce que la plus petite section transversale d'écoulement a une forme elliptique dans la région du contour (9).
  7. Brûleur à prémélange selon l'une quelconque des revendications 1 à 6,
    caractérisé en ce que des étages de turbine d'une installation de turbine à gaz se raccordent à la chambre de combustion (4).
  8. Procédé pour faire fonctionner une chambre de combustion en utilisant un brûleur à prémélange selon l'une quelconque des revendications 1 à 7,
    caractérisé en ce que l'écoulement tourbillonnaire est accéléré et ralenti localement dans la direction axiale de l'écoulement à l'intérieur du générateur de tourbillon (1) ou dans une zone de mélange se raccordant au générateur de tourbillon (1) .
  9. Procédé selon la revendication 8,
    caractérisé en ce que l'accélération axiale de l'écoulement tourbillonnaire a lieu avant le front avant (6) de la zone de reflux (5) qui se forme et le ralentissement a lieu au moins en partie avant le front avant (6) de la zone de reflux (5) qui se forme.
  10. Procédé selon l'une quelconque des revendications 8 à 9,
    caractérisé en ce que l'accélération et le ralentissement ont lieu en utilisant l'effet Bernoulli.
  11. Procédé selon l'une quelconque des revendications 8 à 10,
    caractérisé en ce que le gradient de tourbillon de l'écoulement tourbillonnaire augmente localement dans la direction de l'écoulement.
EP05701493A 2004-01-20 2005-01-12 Brûleur à prémélange et procédé permettant de faire fonctionner une chambre de combustion Not-in-force EP1706672B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH722004 2004-01-20
PCT/EP2005/050105 WO2005068913A1 (fr) 2004-01-20 2005-01-12 Conception de bruleur a premelange et procede permettant de faire fonctionner une chambre de combustion

Publications (2)

Publication Number Publication Date
EP1706672A1 EP1706672A1 (fr) 2006-10-04
EP1706672B1 true EP1706672B1 (fr) 2008-11-19

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EP05701493A Not-in-force EP1706672B1 (fr) 2004-01-20 2005-01-12 Brûleur à prémélange et procédé permettant de faire fonctionner une chambre de combustion

Country Status (6)

Country Link
US (1) US7896646B2 (fr)
EP (1) EP1706672B1 (fr)
CN (1) CN100538183C (fr)
AT (1) ATE414874T1 (fr)
DE (1) DE502005005999D1 (fr)
WO (1) WO2005068913A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8479720B1 (en) 2008-10-16 2013-07-09 Oscar Enrique Figueroa Heating device and method

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3662462D1 (en) 1985-07-30 1989-04-20 Bbc Brown Boveri & Cie Dual combustor
US5193346A (en) * 1986-11-25 1993-03-16 General Electric Company Premixed secondary fuel nozzle with integral swirler
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
US5865609A (en) * 1996-12-20 1999-02-02 United Technologies Corporation Method of combustion with low acoustics
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
ATE237101T1 (de) * 1998-01-23 2003-04-15 Alstom Switzerland Ltd Brenner für den betrieb eines wärmeerzeugers
NO312379B1 (no) 2000-02-14 2002-04-29 Ulstein Turbine As Brenner for gassturbiner
WO2006069861A1 (fr) * 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange

Also Published As

Publication number Publication date
CN1910403A (zh) 2007-02-07
EP1706672A1 (fr) 2006-10-04
US7896646B2 (en) 2011-03-01
US20080227039A1 (en) 2008-09-18
DE502005005999D1 (de) 2009-01-02
CN100538183C (zh) 2009-09-09
WO2005068913A1 (fr) 2005-07-28
ATE414874T1 (de) 2008-12-15

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