EP1802915A2 - Bruleur pour turbine a gaz - Google Patents

Bruleur pour turbine a gaz

Info

Publication number
EP1802915A2
EP1802915A2 EP05801354A EP05801354A EP1802915A2 EP 1802915 A2 EP1802915 A2 EP 1802915A2 EP 05801354 A EP05801354 A EP 05801354A EP 05801354 A EP05801354 A EP 05801354A EP 1802915 A2 EP1802915 A2 EP 1802915A2
Authority
EP
European Patent Office
Prior art keywords
swirl generator
nozzle
premix burner
pressure nozzle
longitudinal axis
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
EP05801354A
Other languages
German (de)
English (en)
Other versions
EP1802915B1 (fr
Inventor
Peter Flohr
Gijsbertus Oomens
Bettina Paikert
Christian Steinbach
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1802915A2 publication Critical patent/EP1802915A2/fr
Application granted granted Critical
Publication of EP1802915B1 publication Critical patent/EP1802915B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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

Definitions

  • the invention relates to a premix burner for a gas turbine, in particular a nozzle for atomizing liquid fuel in a premix burner with a conical swirl generator and a subsequent cylindrical mixing section.
  • Premix burners with a conical swirl generator and a subsequent cylindrical mixing section are known, for example, from EP 918191.
  • the swirl generator which serves as Vormischrange, has conical nested body part, the longitudinal axes are offset from each other. Compressed combustion air passes through tangential inflow channels between the walls of the conical body part into the mixing space of the swirl generator.
  • a fuel is introduced via one or more nozzles or via fuel lines along the tangential Lucaseinströmungskanäle in the mixing chamber and mixed there with the air.
  • Another premix of air and fuel is achieved in the subsequent mixing section, thanks to lossless
  • the mixing section also fulfills the function of avoiding a flashback of the flame from the combustion chamber into which the mixing section opens.
  • DE 4440 558 discloses a premix burner with a conical swirl generator.
  • the fuel is introduced via a nozzle with openings that are not on the longitudinal axis of the nozzle.
  • the angle between the resulting spray cones and the longitudinal axis of the nozzle is in particular greater than the propagation angle of the conical part of the swirl generator.
  • Said fuel nozzle is designed specifically for a premix burner without a cylindrical mixing section.
  • EP 899 508 discloses a premix burner having a swirl generator with a cylindrically formed mixing section as described in the opening paragraph, and in particular a fuel nozzle with nozzle tubes 104 each producing a fuel jet at an injection angle with respect to the central axis of the fuel nozzle which is equal to the angle of propagation of the swirl generator cone.
  • EP 902233 discloses a combined pressure atomizing nozzle for a gas turbine burner with swirl generator, the nozzle body of which has two separate supply channels, one of which has an outlet opening into the mixing chamber of the burner.
  • the nozzle body thus has two different nozzles, a radially outer multi-hole nozzle with decentralized outlet openings and a central, lying on the longitudinal axis nozzle with a centrally arranged outlet opening.
  • the decentralized outlet openings are positioned so that the spray cones are directed into the wake of the conical shells of the swirl generator.
  • This nozzle is operated at full load via the decentrally positioned outlet openings. At partial load, the nozzle is switched to the central outlets to avoid application of fuel oil droplets to the walls of the swirl generator.
  • DE 19536837 discloses an apparatus for injecting fuels with a swirl chamber within the injector or nozzle.
  • the Swirl chamber has a conical constriction in the flow direction, through which the air-fuel mixture flows and finally passes through a lying on the longitudinal axis of the nozzle outlet opening in a burner mixing chamber.
  • the single outlet opening from the nozzle is arranged on the longitudinal axis of the nozzle.
  • a droplet size distribution of the atomized liquid fuel is achieved which allows complete evaporation of the droplets before combustion occurs in the combustion chamber
  • a high-pressure atomizer nozzle which has one or more fuel channels for the supply of liquid fuel into an interior of the nozzle, wherein the liquid fuel is at full load under a pressure of more than 50 bar.
  • the high-pressure atomizer nozzle has at least two outlet channels and openings, through which the liquid fuel emerges from a single interior space in the nozzle into the mixing space of the swirl generator, wherein the outlet channels are arranged decentrally with respect to the longitudinal axis of the nozzle, so that the exiting spray cone on the wake of directed to individual cone shells.
  • the outlet channels and openings of the nozzle are arranged and formed such that the spray cones emanating from the outlet openings have a longitudinal axis which is at an angle with respect to the nozzle Longitudinal axis of the swirl generator and the mixing path, which is smaller than the cone half-angle of the swirl generator.
  • the inventive arrangement of the outlet openings in said angular range affords the advantage that the fuel droplets do not reach the walls of the premix burner and coking of fuel oil droplets on the walls of the swirl generator is avoided.
  • the fuel cone impinges at a shear angle on the incoming between the conical parts of the swirl generator air, which is small enough that the atomized fuel flow maintains a high speed, thereby achieving a high penetration depth in the premix burner and in the combustion chamber.
  • an excessively large orientation angle of the spray cones relative to the longitudinal axis of the swirl generator would lead to the atomized fuel meeting the air inflow earlier and being guided by the air flow to the center of the swirl generator.
  • the exit channels are oriented so that the longitudinal axes of the individual resulting spray cones extend at an angle with respect to the longitudinal axis of the swirl generator, which is smaller than the half angle of the conical shells and greater than 10 °. In a specific embodiment, this angle is in a range of 10 ° to 18 °.
  • a minimum value for this angle will cause the fuel spray cone to not reach too close to the center of the swirl generator. If the atomized fuel comes too close to the center, the pollutant emission values for the premix burner are higher.
  • the nozzle has in its interior a supply channel for fuel, which leads into a single inner space of the nozzle.
  • This interior is connected via the at least two outlet channels with the interior of the swirl generator.
  • the at least two outlet channels of the nozzle are preferably arranged with respect to the nozzle axis in the radially outer half with respect to the longitudinal axis of the nozzle. This causes less fuel to get into the center of the swirl generator.
  • the openings are positioned symmetrically with respect to the longitudinal or central axis of the nozzle, so that an overall axis-symmetrical hollow spray cone is formed. The orientation of the individual spray cone is in turn at an angle smaller than the cone angle of the swirl generator.
  • the high-pressure atomizer nozzle and in particular its outlet channels have a specific internal geometry, which contributes to the desired stability of the spray cone and penetration depths.
  • the nozzle outlet channels which lead from its interior through the nozzle wall into the interior of the swirl generator, wherein the outlet channels in the flow direction have a first cylindrical path, a conically formed constriction and finally a second cylindrical route.
  • the constriction has a predetermined angle to the longitudinal axis of the outlet channel. Preferably, this half angle of the conical constriction is less than 45 °.
  • the longitudinal axes of the outlet channels each extend at an angle to the longitudinal axis of the nozzle, which is smaller than the half angle of the conical parts of the swirl generator.
  • the internal geometry of the exit channels provides the advantage of avoiding turbulence as well as cavitation effects.
  • the high-pressure atomizer nozzle according to the invention differs from the prior art, for example from EP 9022333 in that the nozzle as a whole has a greatly simplified design. Its interior consists of a single inner chamber, which leads to reduced turbulence at the nozzle outlet and a more stable spray cone. It has only one set of outlets through which the liquid fuel is sprayed for all different operating situations and loads. For this purpose, however, the outlet openings have the specific internal geometry according to the invention and alignment with respect to the longitudinal axis of the premix burner.
  • the outlet channels consist of tubes, which from the interior of the nozzle through the wall and extend beyond the surface of the nozzle.
  • the tubes have a length such that they only protrude beyond the surface of the nozzle, but are shorter than the nozzle tip. In another variant, they extend beyond the tip of the nozzle.
  • the outlet channels with said cylindrical sections and conical narrowing lead from the interior of the nozzle through the wall, wherein the outlet opening is located on the outer surface of the nozzle.
  • the outer wall of the nozzle tip is conically formed.
  • the internal geometry of the outlet channels and in particular the narrowing of a given angle in front of the outlet opening into the swirl generator causes a reduction of turbulence in the spray cone and a smaller spread angle of the spray cone. This allows a spray cone with a more uniform velocity profile.
  • the increased flow stability in the spray cone allows improved placement of the fuel in the premix burner and thus improved flame conditions.
  • the second cylindrical sections of the outlet channels each have a length that is at most five times the diameter of the outlet openings. Such a length to diameter ratio contributes to an improvement in the airfoil and flow stability.
  • the outlet openings have a diameter of 0.5 - 1.5 mm.
  • the outer wall of the nozzle tip is formed rounded together with the aforementioned internal geometries of the outlet channels of the nozzle, preferably oval in cross-section.
  • the rounded shape provides further advantages in terms of the air inflow, in that the air flow of this shape can follow the outer wall of the nozzle uniformly and form correspondingly little vortex or recirculation downstream of the nozzle. This increases the homogeneity of the mixing of air and fuel, which causes a lowering of the NOx emission values.
  • a reduced recirculation downstream of the nozzle also influences the swirl at the end of the cylindrical mixing section and leads to an aerodynamic stabilization of the flame in the combustion chamber.
  • Such Stabilization allows a greater freedom in the operating parameters of the burner.
  • the premix burner in the cylinder wall of the mixing section which follows the swirl generator in the flow direction, further openings for the inlet of compressed air.
  • the premix burner has further air inlet channels, which run directly along the high-pressure atomizer nozzle and convey air into the mixing chamber of the swirl generator there.
  • the high-pressure atomizing nozzle according to the invention is suitable not only for use in a premix burner with swirl generator with subsequent mixing section, but also for premixing with swirl generator alone without mixing section.
  • the high pressure atomizer nozzle is positioned so that its tip extends halfway the length of the swirl generator or over half of it.
  • FIG. 1, FIG. 3 a shows a longitudinal section of a preferred embodiment of the nozzle according to the invention
  • FIG. 3b shows a detailed view of the internal geometry of the nozzle of FIG. 3a
  • FIG. 3c shows a variant of the embodiment of FIG. 3a
  • FIG. 4 shows a longitudinal section of a further embodiment of the high-pressure atomizer nozzle and its internal geometry
  • Figure 5 shows an application of the nozzle in a premix burner with a conical
  • FIG. 1 shows a premix burner, for example for a gas turbine. It has a conical swirl generator 1 and a subsequent cylindrical mixing section 2, which opens into a combustion chamber space 3.
  • the swirl generator 1 consists in this example of four nested cone parts 4a, 4b, 4c, 4d, of which in Figure 1, the conical parts 4b and 4d are visible.
  • the individual longitudinal axes of the conical parts are arranged offset from one another and from the longitudinal axis 5 of the swirl generator, as can be seen from FIG.
  • the conical parts 4a-d each extend at an angle ⁇ to the longitudinal axis 5 of the swirl generator 1. Together with their longitudinal edges, they form interspaces 6, which are used for introducing compressed combustion air whose flow profile is indicated by the arrows 7.
  • a high-pressure spray nozzle 10 is arranged for introducing liquid fuel into the swirl generator 1 in the initial part of the conical swirl generator. This is according to the following Figures 3a-c and Figure 4 formed so that an alignment of the spray cone 11 is achieved at an angle ß with respect to the longitudinal axis 5 of the swirl generator, wherein the angle ß smaller than the angle ⁇ , or the half angle of the conical parts of the swirl generator, is. This orientation of the spray cone avoids wetting of the walls of the swirl generator by fuel oil droplets and coking of the walls.
  • further openings 14 are arranged in the outer wall of the cylindrical mixing section 2 for the supply of air into the mixing section. These cause a stabilization of the flame and avoid a flashback.
  • Figure 2 shows in cross-section H-Il the swirl generator 1 with conical parts 4a-d and the centrally arranged on the longitudinal axis of the swirl generator high-pressure atomizer nozzle 10.
  • Arrows 7 indicate the air inflow into the interior of the swirl generator.
  • positions 12a-d are indicated decentralized to the longitudinal axis of the fuel nozzle 10, at which fuel emerges.
  • four opening positions are shown, for example, two or any more positions are possible.
  • the outlet openings are positioned so that the exiting spray cone to the wake of the individual Tapered parts 4a-d is directed.
  • the outlet openings are each arranged on auxiliary lines 13a-d, which run at a right angle to the tangent of the end portion of the conical shells 4a-d.
  • This positioning of the outlet openings and spray cone causes the spray cones are detected by the incoming air flows 7 so that the sprayed fuel reaches a large penetration depth in the premix burner.
  • a different positioning of the spray cones would cause the spray cones to be caught earlier by the air currents compared to the orientation shown and would be directed towards the center of the premix burner, leading to higher emission levels.
  • FIG. 3 a shows a preferred high-pressure atomizer nozzle according to the invention with an outer rounded tip 31 and an inner space 32 which has a conically shaped inner wall 33 towards the tip.
  • two or more tubes 34 pass through the nozzle wall into the interior of the swirl generator, wherein the longitudinal axes 38 of the tubes 34 extend at an angle ⁇ to the longitudinal axis 5 of the nozzle and the swirl generator.
  • the tubes 34 extend over a length such that they protrude beyond the tip of the nozzle.
  • the outer wall of the end portions of the tubes are each preferably rounded.
  • FIG. 3b shows a second variant in which two or more tubes 34 'extend only slightly beyond the outer wall of the nozzle 10, so that they extend less far into the swirl generator than the nozzle tip itself.
  • the nozzle tip is rounded.
  • the flow of air introduced through inlet channels directly along the nozzle is positively affected by this type of nozzle tip in the region and subsequently the nozzle.
  • air recirculations in the area of the nozzle and subsequently the nozzle are reduced, which improves the mixing of fuel and air and reduces the NO x emission values.
  • FIG. 3c shows the inner geometry of the nozzle tubes 34 in detail. In an initial part, these have a first cylindrical path 35 leading away from the interior of the nozzle. In the flow direction follows a conical, narrowing transition section 36 with a cone half-angle ⁇ wall of the constriction with respect to the longitudinal axis 38 of the tube smaller than 45 °, which opens into a second, narrower cylindrical path 37 with a narrower diameter.
  • the length of the second cylindrical section 37 is preferably at most five times the diameter of the outlet opening.
  • a further embodiment of the fuel atomizing nozzle 10 according to FIG. 4 has an inner space 20, which is conical in the flow direction toward the end of the nozzle. From the conically formed tapered end wall 21 of the inner space 20, two or more outlet channels 22 each lead to a first cylindrical section 23, one conical narrowing 24 following in the flow direction and a second narrower cylindrical section 25 which finally leads to an outlet opening 26.
  • the arrows indicate the flow direction of the liquid fuel.
  • the longitudinal axes 27 of the outlet channels which are equal to the longitudinal axes of the resulting spray cone, extend at an angle ⁇ with respect to the longitudinal axis 5 of the nozzle and the swirl generator.
  • the outlet openings 26 are arranged in particular in the radially outer half of the nozzle. Preferably, they have a diameter of 0.5 - 1.5 mm.
  • the nozzle tip 28 is externally conical in the embodiment shown.
  • FIG. 5 shows an application of the high-pressure atomizer nozzle according to the invention in a premix burner with a cone-shaped
  • the swirl generator wherein no mixing section follows the swirl generator, but the swirl generator opens directly into a combustion chamber.
  • the atomizer nozzle extends to half the length of the interior of the swirl generator or further.
  • the nozzle has one of the embodiments with outlet channels according to the figures 3a-c and 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

L'invention concerne un brûleur à prémélange, par exemple pour une turbine à gaz, pourvu d'un générateur de tourbillons (1) conique et d'une section de mélange (2) cylindrique située en aval de celui-ci dans le sens d'écoulement, ce brûleur présentant une buse de pulvérisation haute pression (10) comprenant un ou plusieurs canaux d'amenée du combustible. Cette buse de pulvérisation haute pression (10) présente au moins deux canaux de sortie par lesquels le combustible liquide pénètre dans le générateur de tourbillons (1), ces canaux étant disposés de façon décentrée par rapport à l'axe longitudinal de la buse et étant conçus de telle sorte que le cône de projection (11) du combustible soit orienté selon un angle (ß) par rapport à l'axe longitudinal du générateur de tourbillons (1) inférieur au demi-angle (a) du cône du générateur de tourbillons (1). La géométrie intérieure des canaux de sortie présente en particulier un rétrécissement conique.
EP05801354.1A 2004-10-18 2005-10-07 Bruleur pour turbine a gaz Not-in-force EP1802915B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH17102004 2004-10-18
PCT/EP2005/055098 WO2006042796A2 (fr) 2004-10-18 2005-10-07 Bruleur pour turbine a gaz

Publications (2)

Publication Number Publication Date
EP1802915A2 true EP1802915A2 (fr) 2007-07-04
EP1802915B1 EP1802915B1 (fr) 2016-11-30

Family

ID=34974029

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05801354.1A Not-in-force EP1802915B1 (fr) 2004-10-18 2005-10-07 Bruleur pour turbine a gaz

Country Status (8)

Country Link
US (1) US7520745B2 (fr)
EP (1) EP1802915B1 (fr)
JP (1) JP2008517241A (fr)
CN (1) CN100559080C (fr)
CA (1) CA2584270C (fr)
MX (1) MX2007004119A (fr)
MY (1) MY138700A (fr)
WO (1) WO2006042796A2 (fr)

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Also Published As

Publication number Publication date
WO2006042796A3 (fr) 2006-08-10
EP1802915B1 (fr) 2016-11-30
WO2006042796A2 (fr) 2006-04-27
US20070207431A1 (en) 2007-09-06
MX2007004119A (es) 2007-06-20
CN101044355A (zh) 2007-09-26
JP2008517241A (ja) 2008-05-22
CA2584270A1 (fr) 2006-04-27
MY138700A (en) 2009-07-31
CA2584270C (fr) 2013-07-16
US7520745B2 (en) 2009-04-21
CN100559080C (zh) 2009-11-11

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