EP1781988B1 - Lance pour bruleur hybride - Google Patents

Lance pour bruleur hybride Download PDF

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Publication number
EP1781988B1
EP1781988B1 EP05775906.0A EP05775906A EP1781988B1 EP 1781988 B1 EP1781988 B1 EP 1781988B1 EP 05775906 A EP05775906 A EP 05775906A EP 1781988 B1 EP1781988 B1 EP 1781988B1
Authority
EP
European Patent Office
Prior art keywords
nozzles
passage
lance
nozzle
lance according
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.)
Active
Application number
EP05775906.0A
Other languages
German (de)
English (en)
Other versions
EP1781988A1 (fr
Inventor
Andreas Dr. Brautsch
Daniel Burri
Hanspeter Hardegger
Bettina Dr. Paikert
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 EP1781988A1 publication Critical patent/EP1781988A1/fr
Application granted granted Critical
Publication of EP1781988B1 publication Critical patent/EP1781988B1/fr
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Classifications

    • 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
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/108—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel intersecting downstream of the burner outlet
    • 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
    • F23R3/36—Supply of different fuels

Definitions

  • the invention relates to a lance for a hybrid burner of a combustion chamber of a gas turbine, in particular a gas turbine for a power plant.
  • a liquid fuel for example a suitable oil
  • a gaseous fuel for example natural gas
  • a lance for injecting pre-mixed with combustion air liquid and / or gaseous fuel in a gas turbine engine for example, in the document US 5836163 described.
  • This device allows operation of the gas turbine with liquid or gaseous main fuel and liquid or gaseous pilot fuel.
  • it has a gaseous fuel feeder, a liquid fuel feeder and a compressed combustion air feeder which service the different fuel and combustion air paths.
  • this device comprises a central flow channel (46) for liquid fuel, a coaxially positioned duct (52) for supplying combustion air, another annular channel (54) for gaseous fuel surrounding the latter and terminating in an outlet (55).
  • These three inner channels primarily serve pilots.
  • this device has an annular channel (76) for liquid fuel, a secondary air channel (58), a main air channel (64) and an outer collecting channel (66), from the gaseous main fuel via spokes (68) and openings (70) introduced therein. is injected into the combustion air duct (64) and mixed with the air supplied from the compressor. The resulting mixture is fluidized in the mixing chamber (128) and then exits into the annular combustion chamber (32).
  • An air inlet plate (118) distributes and controls the mass flow of the combustion air supplied by the compressor. By adjusting the air inlet plate (118) and feeding the respective fuel channels with the intended fuel different operating modes of the combustion chamber with liquid or gaseous main fuel with or without pilot support possible.
  • the supply of the lance with the gaseous fuel usually takes place via a pipeline, in which a gas pressure predetermined by the gas supply system prevails.
  • this system pressure present in the pipeline is too low to be able to inject the gaseous fuel with sufficient pressure difference through the lance into the combustion chamber.
  • the installation of such an additional compressor increases the installation cost of the combustion chamber or the equipped gas turbine.
  • the additional compressor for its operation requires energy, which reduces the efficiency of the power plant in a preferred application of the gas turbine in a power plant for power generation.
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, deals with the problem of providing a lance of the type mentioned an improved embodiment, which in particular allows operation of the hybrid burner equipped with a comparatively low pressure in the gaseous fuel, but a ensures certain pressure difference to the gas path, so that the flame front can not migrate into the gas path opposite to the gas flow direction.
  • the invention is based on the general idea of reducing aerodynamic improvements in the gas path of the lance whose flow resistance, thereby reducing the pressure drop occurring in the flow through the lance. As a result, it can lower the pressure required in the gaseous fuel upstream of the lance.
  • the aim is to lower the flow resistance in the gas path of the lance as far as possible so that the remaining pressure drop already a proper operation of the burner with the system pressure prevailing in the pipeline allows. This means that it is then possible to dispense with an additional compressor upstream of the lance.
  • the flow resistance in the gas path of the lance is significantly reduced in particular because, in the case of a distributor section which is arranged upstream of the outer nozzles in the outer channel and which has a plurality of star-shaped, axially extending passage openings for the gaseous fuel, the passage openings are dimensioned in that these each have a larger opening width in the circumferential direction than in the radial direction.
  • the flow-through cross-section in the manifold section is considerably increased, which reduces its flow resistance accordingly.
  • the invention utilizes the knowledge that a particularly serious pressure drop arises during the flow through the distributor section within the lance, so that there is a particularly great potential for the reduction of the flow resistance.
  • the outer channel may be limited axially in the region of the outer nozzles by an outer end wall, whereby the outer channel is axially closed.
  • an axial recess is then formed in the outer end wall on a side remote from the distributor section.
  • a further reduction of the pressure drop in the gas path of the lance can be realized in another embodiment in that with each outer nozzle, a transition from the outer channel to an outer nozzle channel formed in the interior of the respective outer nozzle is provided with an inlet zone tapering in the direction of flow. Such an inlet zone reduces the flow resistance during the deflection of the gas flow, which also reduces the total resistance of the lance.
  • Corresponding Fig. 1 includes a here only partially indicated combustion chamber 1, at least one hybrid burner 2, which is equipped with a lance 3.
  • the combustion chamber 1 is preferably a component of a gas turbine, not shown here, in particular for generating electricity within a power plant.
  • the hybrid burner 2 may burn both gaseous fuels, such as natural gas, and liquid fuels, such as a suitable oil.
  • the lance 3 is connected on the one hand to a liquid fuel supply line 4 and on the other hand to a gas fuel supply line 5.
  • a pump 6 is usually arranged in order to be able to supply the liquid fuel with the required supply pressure.
  • the gas fuel supply line 5 is connected substantially directly to a pipeline, not shown here, which provides the gaseous fuel at a comparatively low pipeline pressure. Due to the inventive design of the lance 3, it is possible to dispense with a compressor in the gas fuel supply line 5 upstream of the lance 3.
  • the burner 2 compressed air is supplied according to an arrow 7 from a compressor, not shown.
  • the lance 3 is introduced with respect to the flow direction of the air 7 substantially radially to the burner 2 and has a projecting into the burner 2, substantially rectangular angled lance head 8.
  • the lance head 8 is thus with respect to its longitudinal central axis 9 parallel to the main flow direction of the supplied air. 7 oriented.
  • the lance head 8 is configured such that it injects the liquid and / or gaseous fuel radially into the burner 2 with respect to its longitudinal central axis 9, that is, with respect to the main flow direction of the air 7 prevailing in the burner 2.
  • Fig. 2 and 3 contains the lance 3 in its head 8 an inner channel 10 for liquid fuel and an outer channel 11 for gaseous fuel.
  • the two channels 10, 11 are arranged coaxially with each other, so that the outer channel 11 surrounds the inner channel 10. Accordingly, the outer channel 11 has an annular cross section, while the inner channel 10 has a full cross section.
  • Inner channel 10 and outer channel 11 are separated by an inner tube 16 and enclosed by a coaxially arranged outer tube 17.
  • the lance 3 is equipped at its head 8 with a plurality of outer nozzles 12, which are arranged in a star shape with respect to the longitudinal central axis 9 and extend radially from the outer channel 11.
  • the outer nozzles 12 each contain an outer nozzle channel 13 which extends radially from the outer channel 11 and communicates with this. Accordingly, the gaseous fuel can be injected into the burner 2 via the outer nozzles 12.
  • the lance 3 is also equipped at its head 8 with internal nozzles 14, which are also arranged in a star shape with respect to the longitudinal central axis 9 and thereby depart radially from the inner channel 10.
  • an inner nozzle 14 is arranged coaxially within an outer nozzle 12, wherein inner nozzles 14 and outer nozzles 12 radially outwardly each ends approximately flush.
  • Each inner nozzle 14 includes an inner nozzle channel 15 which communicates with the inner channel 10. Accordingly, the liquid fuel can be injected into the burner 2 via the inner nozzles 15.
  • the coaxial arrangement of the nozzles 12, 14 results in an annular cross section for the outer nozzle channel 13, while the inner nozzle channel 15 has a full cross section.
  • a distributor section 18 is arranged upstream of the outer nozzles 12, which in Fig. 2 characterized by a curly bracket.
  • the distributor section 18 forms an annularly closed axial section of the lance 3 or of the lance head 8 and may in particular be formed in one piece on the outer tube 17.
  • the distributor section 18 is thus arranged in the flow-through cross section of the outer channel 11.
  • the distributor section 18 is provided with a plurality of star-shaped passage openings 19 which extend axially through the distributor section 18.
  • Such a distributor section 18 is required in order to avoid a damage event in which the lance head 8 z. B. has become leaky due to overheating, to ensure a certain pressure difference to the gas path, so that the flame front can not migrate into the gas path against the gas flow direction and thus not too much fuel can flow uncontrollably into the burner 2.
  • the passage openings 19 are each designed such that they have a larger opening width in the circumferential direction than in the radial direction.
  • the circumferential opening width oriented in the circumferential direction is marked by an arrow 20, while the radially-oriented radial opening width is indicated by an arrow 21.
  • the circumferential opening width 20 is more than twice as large as the radial opening width 21.
  • the circumferential opening width 20 is approximately three to five times larger, preferably approximately four times larger than the radial opening 21.
  • the passage openings 19 extend in the circumferential direction in each case along a circular arc segment, as a result of which a particularly large flow-through cross section for the respective passage openings 19 can be achieved.
  • a particularly large flow-through cross section for the respective passage openings 19 can be achieved.
  • other cross-sectional geometries may also be used, for example elliptical cross sections.
  • the individual passage openings 19 are separated from one another in the circumferential direction by webs 22.
  • the webs 22 extend radially and axially with respect to the longitudinal central axis 9. Compared to the through holes 19, these webs 22 have only a comparatively small cross section.
  • the circumferential opening width 20 of the through openings 19 is at least three times greater than a wall thickness 23 of the webs 22 measured in the circumferential direction.
  • the webs 22 are dimensioned such that the circumferential opening width 20 of the through openings 19 is approximately four to eight times greater than the wall thickness 23 Footbridges 22.
  • the outer channel 11 is axially closed by an outer end wall 24 in the region of the outer nozzle 12. Since the outer nozzles 12 and the outer nozzle channels 13th With respect to the outer channel 11 are radially oriented, it comes at a transition 25 between the outer channel 11 and outer nozzle channel 13 to a relatively strong flow deflection, which in Fig. 4 is shown by arrows.
  • an axial recess 26 can be recessed in the outer end wall 24 in each outer nozzle 12 at a side facing away from the distributor section 18, according to an advantageous embodiment. This depression 26 makes it easier for the gas flow in the inner channel 11 to flow around the respective inner nozzle 14.
  • the depressions 26 can - as here in Fig. 4 shown - be provided separately for each outer nozzle 12, in which case an embodiment is preferred in which the recess 26 is configured with respect to a longitudinal central axis 27 of the nozzles 12, 14 circular arc segment-shaped. As a result, so-called "dead water areas" can be reduced and the flow resistance can be lowered.
  • Particularly favorable values for the pressure drop at the transition 25 can be achieved if the dimensioning of the recess 26 is matched to the dimension of the outer nozzle channel 13 in a special way.
  • Cheap is for example, an embodiment in which a relative to the longitudinal central axis 27 of the outer nozzle 12 measured radial depth 28 is about twice or at least twice greater than a radial distance 29 between an unspecified inner wall of the outer nozzle 12 and an unspecified outer wall of the inner nozzle 14 arranged therein ,
  • the transition 25 Another measure for reducing the pressure loss within the lance 3 is seen in an aerodynamic optimization of the transition 25.
  • the transition 25 according to Fig. 4 be equipped with an inlet zone 30, which tapers in the flow direction.
  • the taper of the inlet zone 30 can be achieved by a simple chamfering. It is also possible to design the rejuvenation rounded.
  • a divider 31 is suitably arranged in the inner channel 10 in the region of the inner nozzles 14.
  • the divider 31 includes a core 32 that extends concentrically within the inner channel 10.
  • dividing walls 33 are formed, which extend radially and axially and thereby protrude from the core 32 in a star shape, such that they touch the inner tube 16.
  • the core 32 and the partition walls 33 are designed swept in the direction of flow to the longitudinal central axis 9. With the help of such a divider 31, the deflection of the liquid flow in the inner channel 10 can be improved on the inner nozzle 14.
  • a distance 34 between the core 32 and the inner tube 16 is at least twice greater than a core diameter 35.
  • the inner tube 16 in the region of the divider 31 is not or only slightly widened in order to ensure the most constant flow cross-section up to the inner nozzle 14 can.
  • the outer channel 16 may have a larger flow cross-section in the region of the outer nozzles 12, so that even in the outer channel 11 to the outer nozzles 12 as constant a flow cross-section can be achieved.
  • this measure ultimately leads to a reduction of the flow resistance in the gas path of the lance.
  • a transition 37 from the core 32 to the inner end wall 36 may now be configured kehlförmig.
  • an axial length 38 is preferred, which is about the same size as or may be smaller than an opening cross section 39 of the inner channel 10 in the region of the inner nozzle 14. This relatively short divider 31 in turn allows expansion in the outer channel 11 and leads there to a reduced flow resistance.

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)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)

Claims (12)

  1. Lance pour brûleur hybride (2) d'une chambre de combustion (1) d'une turbine à gaz,
    - comportant un canal intérieur central (10) pour un combustible liquide,
    - comportant un canal extérieur (11) pour un combustible gazeux, entourant coaxialement le canal intérieur (10),
    - comportant plusieurs buses extérieures (12) disposées en forme d'étoile, sortant radialement du canal extérieur (11),
    - comportant plusieurs buses intérieures (14) sortant radialement du canal intérieur (10), qui s'étendent respectivement coaxialement à l'intérieur d'une des buses extérieures (12),
    caractérisée en ce que
    dans le canal extérieur (11) et en amont des buses extérieures (12) une section de distributeur (18) est disposée, qui présente plusieurs ouvertures traversantes (19) pour le combustible gazeux disposées en forme d'étoile, s'étendant coaxialement, qui présentent respectivement dans la direction circonférentielle une plus grande largeur d'ouverture que dans la direction radiale.
  2. Lance selon la revendication 1, caractérisée en ce que les ouvertures traversantes (19) s'étendent respectivement dans la direction circonférentielle le long d'un segment d'arc de cercle.
  3. Lance selon la revendication 1 ou 2, caractérisée en ce que les ouvertures traversantes (19) sont délimitées dans la direction circonférentielle par des gradins (22) s'étendant radialement et axialement et la largeur d'ouverture (20) des ouvertures traversantes (19) dans la direction circonférentielle est au moins trois environ quatre à huit fois plus grande qu'une épaisseur de paroi (23) des gradins (22) dans la direction circonférentielle.
  4. Lance selon une des revendications 1 à 3, caractérisée en ce que le canal extérieur (11) est obturé axialement au niveau des buses extérieures (12) par une paroi frontale extérieure (24) et en ce que sur chaque buse extérieure (12) une cavité axiale (26) est ménagée sur un côté qui se détourne de la section de distributeur (18) dans la paroi frontale extérieure (24).
  5. Lance selon la revendication 4, caractérisée en ce que pour chaque buse extérieure (12) une cavité (26) séparée est prévue.
  6. Lance selon la revendication 5, caractérisée en ce que la cavité (26) est réalisée coaxialement à la buse extérieure (12) en forme de segment d'arc de cercle.
  7. Lance selon la revendication 4, caractérisée en ce que pour toutes les buses extérieures (12) une cavité commune (26) est prévue, qui s'étend en forme d'anneau fermé dans la direction circonférentielle.
  8. Lance selon une des revendications 4 à 7, caractérisée en ce que la cavité (26) présente par rapport à un axe médian longitudinal (27) de la buse extérieure respective (12) une profondeur radiale (28), qui est au moins deux fois plus grande qu'un espacement radial (29) entre une paroi intérieure de la buse extérieure (12) et une paroi extérieure de la buse intérieure (14) disposée dans cette dernière.
  9. Lance selon une des revendications 1 à 8, caractérisée en ce que sur chaque buse extérieure (12) une transition (25) du canal extérieur (11) à un canal de buse extérieure (13) réalisé à l'intérieur de la buse extérieure respective (12) est pourvu d'une zone d'introduction (30) allant en s'amincissant dans la direction d'écoulement.
  10. Lance selon une des revendications 1 à 9, caractérisée en ce que dans la région de buse intérieure (14) dans le canal intérieur (10) un diviseur (31) est disposé, qui présente un noyau (32) disposé concentriquement par rapport au canal intérieur (10) ainsi que des parois de séparation (33) s'étendant radialement et axialement, dépassant de ce dernier en forme d'étoile jusqu'à un tuyau intérieur (16) délimitant le canal intérieur (10) radialement à l'extérieur, et en ce que un espacement (34) entre le noyau (32) et le tuyau intérieur (16) est au moins deux fois plus grand qu'un diamètre de noyau (35).
  11. Lance selon la revendication 10, caractérisée en ce que le noyau (32) dépasse en saillie axialement d'une paroi frontale intérieure (36) obturant axialement le canal intérieur (10) dans la région des buses intérieures (14), et en ce que une transition (37) du noyau (32) à la paroi frontale intérieure (36) est réalisée en forme de gorge en coupe longitudinale.
  12. Lance selon la revendication 10 ou 11, caractérisée en ce que une longueur axiale (38) du noyau (32) est aussi grande que ou plus petite qu'une section transversale d'ouverture (39) du canal intérieur (10) dans la région des buses intérieures (14).
EP05775906.0A 2004-08-23 2005-08-18 Lance pour bruleur hybride Active EP1781988B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004041272.3A DE102004041272B4 (de) 2004-08-23 2004-08-23 Hybridbrennerlanze
PCT/EP2005/054073 WO2006021541A1 (fr) 2004-08-23 2005-08-18 Lance pour bruleur hybride

Publications (2)

Publication Number Publication Date
EP1781988A1 EP1781988A1 (fr) 2007-05-09
EP1781988B1 true EP1781988B1 (fr) 2015-09-30

Family

ID=35045074

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05775906.0A Active EP1781988B1 (fr) 2004-08-23 2005-08-18 Lance pour bruleur hybride

Country Status (8)

Country Link
US (1) US7963764B2 (fr)
EP (1) EP1781988B1 (fr)
CA (1) CA2577770C (fr)
DE (1) DE102004041272B4 (fr)
ES (1) ES2556165T3 (fr)
MX (1) MX2007001887A (fr)
TW (1) TWI366648B (fr)
WO (1) WO2006021541A1 (fr)

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EP2199674B1 (fr) * 2008-12-19 2012-11-21 Alstom Technology Ltd Brûleur d'une turbine à gaz avec une configuration spéciale de lance
US20100192582A1 (en) * 2009-02-04 2010-08-05 Robert Bland Combustor nozzle
EP2388520B1 (fr) * 2010-05-20 2016-10-26 General Electric Technology GmbH Lance d'un brûleur d'une turbine à gaz
US8671691B2 (en) * 2010-05-26 2014-03-18 General Electric Company Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor
US20110314827A1 (en) * 2010-06-24 2011-12-29 General Electric Company Fuel nozzle assembly
EP2789915A1 (fr) * 2013-04-10 2014-10-15 Alstom Technology Ltd Procédé de fonctionnement d'une chambre de combustion et chambre de combustion
WO2015069354A2 (fr) * 2013-08-30 2015-05-14 United Technologies Corporation Double gicleur de combustible avec atomisation par filmage liquide pour turbine à gaz
US10125991B2 (en) 2014-08-14 2018-11-13 Siemens Aktiengesellschaft Multi-functional fuel nozzle with a heat shield
US10132240B2 (en) 2014-08-14 2018-11-20 Siemens Aktiengesellschaft Multi-functional fuel nozzle with a dual-orifice atomizer
CN106574774A (zh) 2014-08-14 2017-04-19 西门子公司 具有雾化器阵列的多功能燃料喷嘴
EP3073097B1 (fr) * 2015-03-27 2019-06-12 Ansaldo Energia Switzerland AG Système de distribution de carburant double intégré
US10571128B2 (en) * 2015-06-30 2020-02-25 Ansaldo Energia Ip Uk Limited Gas turbine fuel components
USD849226S1 (en) * 2017-05-24 2019-05-21 Hamworthy Combustion Engineering Limited Atomizer
EP3657072B1 (fr) * 2018-11-23 2021-08-11 Ansaldo Energia Switzerland AG Lance pour un brûleur et un procédé de modernisation d'une lance
WO2021261431A1 (fr) * 2020-06-26 2021-12-30 三菱パワー株式会社 Dispositif d'injection de carburant, chambre de combustion comprenant un dispositif d'injection de carburant et turbine à gaz comprenant une chambre de combustion

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Also Published As

Publication number Publication date
CA2577770A1 (fr) 2006-03-02
ES2556165T3 (es) 2016-01-13
TWI366648B (en) 2012-06-21
DE102004041272A1 (de) 2006-03-02
DE102004041272B4 (de) 2017-07-13
CA2577770C (fr) 2013-03-12
US20070207425A1 (en) 2007-09-06
EP1781988A1 (fr) 2007-05-09
WO2006021541A1 (fr) 2006-03-02
MX2007001887A (es) 2008-10-29
US7963764B2 (en) 2011-06-21
TW200617323A (en) 2006-06-01

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