EP1344002B1 - Bruleur a introduction etagee du carburant - Google Patents

Bruleur a introduction etagee du carburant Download PDF

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Publication number
EP1344002B1
EP1344002B1 EP01970076A EP01970076A EP1344002B1 EP 1344002 B1 EP1344002 B1 EP 1344002B1 EP 01970076 A EP01970076 A EP 01970076A EP 01970076 A EP01970076 A EP 01970076A EP 1344002 B1 EP1344002 B1 EP 1344002B1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
combustion air
swirl
group
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
Application number
EP01970076A
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German (de)
English (en)
Other versions
EP1344002A1 (fr
Inventor
Adnan Eroglu
Douglas Pennell
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.)
General Electric Technology GmbH
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 EP1344002A1 publication Critical patent/EP1344002A1/fr
Application granted granted Critical
Publication of EP1344002B1 publication Critical patent/EP1344002B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex

Definitions

  • the present invention relates to a staged fuel injection combustor composed of a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, wherein the means for introducing fuel into the combustion air stream comprises at least a first fuel supply having a first group Fuel outlet openings and a second fuel supply to a second group of fuel outlet openings downstream of the first group of fuel outlet openings and the first and second group of fuel outlet openings and inlet openings for the combustion air flow along the swirl space formed by the swirl generator are arranged.
  • a preferred field of application for such a burner is the use in steam and gas turbine technology.
  • a multi-shell cone-shaped burner known as a double-cone burner. Due to the conical multi-shell vortex generator, which forms a swirl space in the interior, a closed swirl flow is generated in the conical head, which becomes unstable due to the increasing swirl along the conical tip and into an annular Swirl flow merges with backflow in the core.
  • the shells of the swirl generator are assembled in such a way that tangential air inlet slots for combustion air are formed along the burner axis. Feed lines for the premix gas, ie the gaseous fuel, are provided on the inflow edge of the conical shells, which have outlet openings for the premix gas distributed along the swirl space in the direction of the burner axis.
  • the gas is injected through the outlet openings or bores transversely to the air inlet gap. This injection, in conjunction with the swirl generated in the swirl space of the combustion air-fuel gas flow to a good mixing of the fuel or premixed gas with the combustion air. Good mixing in such premix burners is the prerequisite for low NO x values during the combustion process.
  • a burner for a heat generator known, which has an additional mixing section for further mixing of fuel and combustion air following the swirl generator.
  • This mixing section can be designed, for example, as a downstream tube, into which the flow emerging from the swirl generator is transferred without appreciable flow losses. Through this additional mixing section, the degree of mixing can be further increased and thus the pollutant emissions can be reduced.
  • Fig. 1 shows schematically an example of such a burner, in which the fuel over Outlet openings in along the burner axis arranged in the swirl body 1 supply channels with the incoming combustion air is mixed.
  • the conical swirl body 1 of the burner is shown with the swirl space 1a enclosed by the latter, along which the fuel feeds to the outlet openings 2 - in the figure indicated by arrows for injected fuel - run.
  • These fuel feeds are generally formed as individual channels, which have a fixed distribution of the fuel outlet openings 2 along the burner axis.
  • a piloting lance 5 via which the fuel is injected directly into the swirl chamber 1a when starting the burner.
  • a switchover from this pilot stage to the premix mode takes place in which the fuel is mixed with the inflowing combustion air via the aforementioned fuel outlet openings 2.
  • WO 93/17279 Another known burner geometry of a premix burner is known from WO 93/17279 known.
  • a cylindrical swirl generator is used with an additional conical inner body.
  • the premix gas is also injected via feeders with corresponding outlet openings in the swirl space, which are arranged along the axially extending air inlet slots.
  • the piloting supply of this burner is provided at the end of the conical inner body.
  • the piloting leads to increased NO x emissions, since in this mode of operation only an insufficient mixing with the combustion air can take place.
  • a burner assembly in which the means for introducing fuel into the combustion air stream at least a first fuel supply to a first group of fuel outlet openings for a first premix fuel quantity and a second fuel supply to a second group of fuel Outlet openings downstream of the first group of fuel outlet openings for a second Premix fuel quantity include.
  • the fuel feeds with the fuel outlet openings are in this case arranged on the swirl body along the swirl space in the longitudinal direction of the burner and divided into at least two mutually independent channels for the fuel.
  • the operation of the burner can be optimally adapted to the respective operating load in terms of emissions.
  • a fuel supply via the piloting lance is no longer necessary because the sole operation with fuel outlet openings of the first stage (eg 2a in Fig. 2 ) causes sufficiently high local temperatures on the burner axis, while the total adiabatic temperature is still low.
  • the extinction limit of a burner with a fully premixed fuel-air mixture has an extinguishing limit above 1600 K.
  • Modern AAP gas turbines are operated at idle and at low load with a fuel-air mixture, the combustion of an adiabatic temperature of 900 produced up to 1600 Kelvin. It is therefore impossible to burn the fuel in the entire available combustion air, so that an enrichment of the core air in the burner by piloting in the region of the burner neck is required.
  • This relates in particular to the abovementioned burners of the prior art with single-stage fuel injection.
  • Applicant's multi-stage fuel injection burners by splitting the fuel feeds into two separate regions, show a reduction in NO x emissions and in the magnitude of combustion pulsations at higher flame temperatures above 1650K.
  • the problem of pulsations still occurs Temperatures below 1500 K, when the first stage is operated essentially alone and thus performs a function similar to a piloting stage.
  • the object of the present invention is to provide a burner which generates a low level of pulsations even at lower combustion temperatures below 1600K.
  • the present staged fuel injection burner is essentially composed of a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream.
  • the means for introducing fuel into the combustion air stream include at least a first fuel supply having a first group of fuel discharge ports and a second fuel supply having a second group of fuel discharge ports remote from the first group of fuel discharge ports.
  • the two groups of fuel outlets as well Inlet openings for combustion air, as a rule air inlet slots, are hereby arranged along the swirl space formed by the swirl body, as is also the case with single-stage burner systems of the type mentioned at the beginning. This is inevitably required to inject the fuel into the combustion air entering through the inlet slots in order to achieve the best possible mixing in this way.
  • the present burner is characterized in that in the transition region between the first group and the second group of fuel outlet openings, a separating element is arranged in the swirl space, which extends in the direction of the combustion chamber and the combustion air flow entering in the region of the first group via the air inlet openings separates from the entering in the second group of fuel-discharge openings combustion air flow.
  • This separation takes place here at least over a region of the swirl space, ie, starting from the transition region in the direction of the combustion chamber into the region of the swirl space into which the second group of fuel outlet openings is arranged.
  • the separating element can be constructed in one piece as well as in several parts. It is preferably composed of a burner axis enclosing the partition.
  • the partition wall is preferably tubular in adaptation to the geometric shape of the swirl generator over at least one subregion.
  • This embodiment of the present burner allows a stronger pulsation even at low load of the system, ie at low burner power and low total adiabatic combustion temperatures.
  • the inventors have recognized that the flame during operation of the first stage without such a separator on the one hand can perform relatively free axial pulsations and on the other hand these pulsations are supported due to the cooling effect of flowing in the second stage through the air inlet openings combustion air.
  • By inserting the separating element between the air streams which flow into the swirl space in the region of the first stage and the air streams which flow in the region of the second stage an interaction between these can be prevented at low burner power. This in turn leads advantageously to a reduction of the combustion pulsations.
  • the burner comprises a fuel lance which extends into the region of the separating element or of the volume formed by the separating element.
  • This burner lance is thus extended compared to the known from the prior art in connection with the burners with single-stage fuel injection fuel or pilot lances.
  • an additional stabilization point for the fuel-air mixture is created by the "increment" over the lance tip of the first stage and the axial pulsation of the combustion is further reduced.
  • the walls of the separating element on cooling channels, which combustion air is supplied from upstream of the swirl generator.
  • the cooling channels extend in the direction of the combustion chamber.
  • the cooling air exits through corresponding openings at the combustion chamber end of the separating element in the swirl space.
  • the separating element is preferably formed integrally with or attached to the swirl body or shells forming it.
  • the present embodiment of the burner makes it possible to provide existing burner designs without expensive redesign with the separating element.
  • Fig. 1 shows a single-stage burner system, as is known from the prior art and has already been explained in the introduction to the description.
  • a burner geometry is used, as in principle from the above-mentioned prior art, in particular from EP 0 321 809 B1 is known.
  • the burner consists of the swirl body 1, which includes a swirl space 1a for mixing the fuel with the combustion air entering via the air inlet slots in the swirl body 1 (indicated by arrows).
  • the combustion chamber 3 connects.
  • the swirl generator 1 is conical in a known manner and consists of several subshells. In these subshells, the channel-shaped feeds 4a and 4b are arranged for the injection of the fuel in the swirl space 1a.
  • a two-stage fuel injection is used, in which a first stage is formed by the fuel supply 4a and a second stage by the fuel supply 4b.
  • the first group of fuel outlet openings 2a in the first fuel channel 4a and the second group of fuel outlet openings 2b in the second fuel channel 4b can be seen schematically.
  • outlet openings 2a, 2b are shown only schematically in the present example, wherein the number, distribution and geometry of these outlet openings is adapted to the respective conditions.
  • the feed line 6 of the fuel to the second stage 4b is guided along the outer wall of the swirl body 1 in this example.
  • the feeder for the first stage 4a is not explicitly shown in this example.
  • a fuel lance 5 can be seen, which extends on the longitudinal axis 7 of the burner.
  • a separating element 8 is provided, that surrounds the longitudinal axis 7 of the burner in the swirling space 1a and is substantially cylindrical or cup-shaped.
  • This separating element 8 separates the combustion air flow entering through the air inlet slots in the region of the first step 4a from the combustion air flow which enters the outer zone of the swirl space 1a in the region of the second step 4b.
  • the flow pattern of the incoming combustion air can be recognized by the two arrows.
  • the separating element 8 in this case forms a kind of can open to the combustion chamber 3.
  • the fuel lance 5 is opposite in this example known arrangements extended and extends to about halfway into the volume formed by the partition 8.
  • the fuel is directed mainly through the fuel outlet openings 2a of the first stage 4a into the inner zone of the swirl space 1a, i. into the entering into the swirl space in this area combustion air, injected.
  • a combustion zone forms on the combustion chamber side edge of the separating element 8, which is shown schematically by the reference numeral 9 in the figure.
  • This combustion of the fuel of the first stage 4a in the said mode of operation is not disturbed by the combustion air flow entering in the region of the second stage 4b, since the flame root is located inside the separating element. Possible pulsations of the combustion are thereby significantly reduced and the stability of the flame is improved, in particular by the extended fuel lance 5, which generates a step backwards facing step.
  • cooling system for the separating element 8 in the form of cooling channels 11 can also be seen very well. These cooling channels 11 are connected to the combustion air entering the swirl generator 1 upstream of the second stage and have their outlet openings at the combustion chamber end of the walls of the separating element 8. The exiting combustion air is indicated in this area by the arrows.
  • the present invention is also applicable to other burner geometries, which are operated via an at least two-stage injection of the fuel into the combustion air.
  • the essential element here is the separating element which separates the combustion air flow entering in the region of the two stages. This separation is required at least in a portion of the swirl space.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)

Claims (6)

  1. Brûleur à injection étagée de combustible, essentiellement constitué d'un tourbillonneur (1) pour un écoulement d'air de combustion et de moyens d'amenée de combustible dans l'écoulement d'air de combustion,
    les moyens d'amenée de combustible dans l'écoulement d'air de combustion comprenant au moins une première amenée de combustible (4a) dotée d'un premier groupe d'ouvertures (2a) de sortie de combustible et une deuxième amenée de combustible (4b) dotée d'un deuxième groupe d'ouvertures (2b) de sortie de combustible situé en aval du premier groupe d'ouvertures (2a) de sortie de combustible, le premier et le deuxième groupe d'ouvertures (2a, 2b) de sortie de combustible ainsi que des ouvertures d'entrée d'air de combustion étant disposés le long d'un espace de tourbillonnage (1a) formé par le tourbillonneur (1), caractérisé en ce que
    dans la zone de transition entre le premier et le deuxième groupe d'ouvertures (2a, 2b) de sortie de combustible, un élément de séparation (8) qui sépare un premier écoulement d'air de combustion qui pénètre dans l'espace de tourbillonnage (1a) dans la zone du premier groupe d'ouvertures (2a) de sortie de combustible d'un deuxième écoulement d'air de combustion qui pénètre dans l'espace de tourbillonnage (1a) dans la zone du deuxième groupe d'ouvertures (2b) de sortie de combustible est disposé dans l'espace de tourbillonnage (1a) au moins sur une partie de l'axe longitudinal (7) du brûleur.
  2. Brûleur selon la revendication 1, caractérisé en ce que l'élément de séparation (8) est formé par une ou plusieurs parois de séparation qui entourent l'axe longitudinal (7) du brûleur.
  3. Brûleur selon les revendications 1 ou 2, caractérisé en ce que l'élément de séparation (8) est configuré essentiellement en forme de tube ou de cuvette.
  4. Système de brûleur selon l'une des revendications 1 à 3, caractérisé en ce que l'élément de séparation (8) est traversé par des canaux de refroidissement (11).
  5. Système de brûleur selon la revendication 4, caractérisé en ce que les canaux de refroidissement (11) présentent des ouvertures de sortie en direction de la chambre de combustion (3).
  6. Système de brûleur selon l'une des revendications 1 à 5, caractérisé en ce que le brûleur présente une lance centrale à combustible (5) qui s'étend dans le volume formé par l'élément de séparation (8).
EP01970076A 2000-10-16 2001-10-03 Bruleur a introduction etagee du carburant Expired - Lifetime EP1344002B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10051221A DE10051221A1 (de) 2000-10-16 2000-10-16 Brenner mit gestufter Brennstoff-Eindüsung
DE10051221 2000-10-16
PCT/IB2001/001817 WO2002033324A1 (fr) 2000-10-16 2001-10-03 Bruleur a introduction etagee du carburant

Publications (2)

Publication Number Publication Date
EP1344002A1 EP1344002A1 (fr) 2003-09-17
EP1344002B1 true EP1344002B1 (fr) 2008-02-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP01970076A Expired - Lifetime EP1344002B1 (fr) 2000-10-16 2001-10-03 Bruleur a introduction etagee du carburant

Country Status (7)

Country Link
US (2) US20040053181A1 (fr)
EP (1) EP1344002B1 (fr)
JP (1) JP4143404B2 (fr)
CN (1) CN1232762C (fr)
AU (1) AU2001290189A1 (fr)
DE (2) DE10051221A1 (fr)
WO (1) WO2002033324A1 (fr)

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EP2538139A2 (fr) 2011-06-20 2012-12-26 Alstom Technology Ltd Procédé de fonctionnement d'un dispositif de combustion ainsi que le dispositif de combustion destiné à la mise en oeuvre du procédé

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RU2755240C2 (ru) * 2017-12-26 2021-09-14 Ансальдо Энергия Свитзерленд Аг Горелка для камеры сгорания газотурбинной энергосиловой установки, камера сгорания газотурбинной энергосиловой установки, содержащая такую горелку, и газотурбинная энергосиловая установка, содержащая такую камеру сгорания
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2538139A2 (fr) 2011-06-20 2012-12-26 Alstom Technology Ltd Procédé de fonctionnement d'un dispositif de combustion ainsi que le dispositif de combustion destiné à la mise en oeuvre du procédé
US9249979B2 (en) 2011-06-20 2016-02-02 Alstom Technology Ltd. Controlling a combustion device to lower combustion-induced pulsations by changing and resetting fuel stagings at different rates of change

Also Published As

Publication number Publication date
CN1232762C (zh) 2005-12-21
JP2004514867A (ja) 2004-05-20
AU2001290189A1 (en) 2002-04-29
US7189073B2 (en) 2007-03-13
WO2002033324A1 (fr) 2002-04-25
US20050175948A1 (en) 2005-08-11
DE10051221A1 (de) 2002-07-11
EP1344002A1 (fr) 2003-09-17
US20040053181A1 (en) 2004-03-18
DE50113673D1 (de) 2008-04-10
CN1524172A (zh) 2004-08-25
JP4143404B2 (ja) 2008-09-03

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