EP1754002A2 - Injecteur pour carburant liquide et bruleur a premelange etage pourvu dudit injecteur - Google Patents

Injecteur pour carburant liquide et bruleur a premelange etage pourvu dudit injecteur

Info

Publication number
EP1754002A2
EP1754002A2 EP05749973A EP05749973A EP1754002A2 EP 1754002 A2 EP1754002 A2 EP 1754002A2 EP 05749973 A EP05749973 A EP 05749973A EP 05749973 A EP05749973 A EP 05749973A EP 1754002 A2 EP1754002 A2 EP 1754002A2
Authority
EP
European Patent Office
Prior art keywords
swirl
injector
nozzle
premix burner
fuel
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
EP05749973A
Other languages
German (de)
English (en)
Other versions
EP1754002B1 (fr
Inventor
Stefano Bernero
Christian Jörg Motz
Tom Strebel
Martin Zajadatz
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 EP1754002A2 publication Critical patent/EP1754002A2/fr
Application granted granted Critical
Publication of EP1754002B1 publication Critical patent/EP1754002B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/34—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
    • 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
    • F23D11/106—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 meeting at the burner outlet
    • F23D11/107—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 meeting at the burner outlet at least one of both being subjected to a swirling 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
    • F23D11/10—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
    • F23D11/16—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 in which an emulsion of water and fuel is sprayed
    • 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
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • 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
    • 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
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • Liquid fuel injector and staged pre-burner with this injector Liquid fuel injector and staged pre-burner with this injector
  • the present invention relates to an injector for liquid fuel with a swirl nozzle for injecting the liquid fuel, which is surrounded by a screen air duct.
  • the invention further relates to a staged premix burner, in particular for a combustion chamber of a gas turbine, with a swirl generator for a combustion air flow, fuel outlet openings for the gradual introduction of gaseous fuel into the combustion air flow and a central carrier which has an injector with a swirl nozzle for the injection of Has liquid fuel and an umbrella air duct.
  • Premix burners are often used in gas turbine plants, in which incoming combustion air is subjected to a swirl and is mixed with the fuel by injecting fuel into a premixing area.
  • the premix burners When used in gas turbines, the premix burners must cover the entire operating range with sufficient security. This operating range also includes, for example, starting up the gas turbine, in which when the burner is ignited, a fuel / air mixture must be combusted at combustion pressures and preheating temperatures close to the ambient conditions. To ensure the stability of the burner operation, the burner is in - 2 - B03 / 207-0 SF
  • this operating area is usually operated with a pilot stage.
  • this pilot stage is arranged centrally in the burner flow field, for example in the form of a fuel lance.
  • the fuel is added to the combustion air axially in the flow direction at the tip of the fuel lance via an injector so that there are fuel-rich zones in the flow field of the burner, thus ensuring stable operation without extinguishing the flame even at low combustion pressures and temperatures.
  • the injection of fuel is generally reduced via the pilot stage for reducing pollutants and the burner is operated in advantageous premix mode.
  • the burner should be usable either for gaseous and liquid fuels.
  • the fuel injector has an annular gap on the fuel lance, from which a small amount of air flows out, based on the total burner airflow. This so-called shielding air shields the two fuel nozzles for liquid and gaseous fuel against unwanted backflows.
  • FIG. 1 An example of an embodiment of such a known premix burner is shown in highly schematic form in FIG. 1 in side view (left) and top view (right).
  • the swirl generator 1 is formed from two partial shells, which are assembled to form a cone-shaped swirl body.
  • Air inlet slots 2 for the tangential entry of combustion air lie between the two partial shells, which are indicated in the figure by the arrows which can be seen at this point. In premix mode, this is along
  • Air inlet slots are introduced into the combustion air via undetectable feeders and fuel outlet openings in order to mix with the combustion air within the volume specified by the swirl generator 1.
  • a fuel lance 3 can be seen centrally within the burner, at the end of which an injector 4 with nozzle openings for the injection of liquid fuel, gaseous fuel and for the discharge of shielding air is attached.
  • the nozzle opening 7 for the introduction of gaseous fuel 7a can be seen in the right part of the figure in the center of the fuel lance 3. This nozzle opening 7 is surrounded by a gap 5 for the exit of shielding air 5a.
  • the annular nozzle opening 6 in the present case for the introduction of liquid fuel ⁇ a forms the outer region of this injector 4.
  • this premix burner is operated exclusively with one of the two pilot stages, ie by injecting - 4 - B03 / 207-0 SF
  • liquid fuel 6a or gaseous fuel 7a via the injector 4 of the fuel lance 3.
  • the upper load range in the case of gaseous fuels, it is necessary to switch completely to the premixing stage in pilot operation due to the high pollutant emissions.
  • an emulsion of water and oil is burned as a liquid fuel in the upper load range.
  • the flame temperature is lowered locally in the flow field. This leads to a reduction in pollutant emissions, especially nitrogen oxide emissions.
  • combustion pulsations must also be avoided in the upper load range, which can lead to restrictions in the operating range.
  • swirl injectors also known as pressure swirl injectors. Because of the high throughput and the limited space available in the area of the tip of the fuel lance, however, such swirl injectors cause a high pressure drop on the fuel side.
  • the object of the present invention is to provide an injector for liquid fuel and a premix burner with such an injector, which achieve good atomization quality with a low pre-pressure of the liquid fuel.
  • the present injector for liquid fuel comprises a swirl nozzle for injecting the liquid fuel and an umbrella air duct surrounding the swirl nozzle.
  • liquid fuel means not only pure fuel, such as oil, but also a mixture or emulsion of this fuel with other substances, in particular an oil / water emulsion.
  • the swirl nozzle has an internal swirl generator for the liquid fuel flowing through and widens in the area of the swirl generator to an enlarged flow cross section, which is reduced again towards the outlet opening of the swirl nozzle.
  • the lance which is stepped on the gas side, leaves more space for a larger nozzle than conventional injectors, which means that pressure loss can be reduced. This enables the operation of this injector with a low pre-pressure and still good atomization quality.
  • the swirl generator inside the nozzle is preferably designed as a swirl grille, which can extend, for example, around a central swirl body within the nozzle. Furthermore, it is advantageous to likewise arrange a swirl generator within the shield air duct surrounding the swirl nozzle.
  • the two swirl generators can produce both swirl in the same direction and in the opposite direction. The generation of a - 6 - B03 / 207-0 SF
  • opposite swirl of the shielding air compared to the internal swirl generator can have a positive influence on the atomization quality of the escaping liquid fuel.
  • the strength and direction of the twist can be used to generate one for each
  • Exit area i.e. in particular the boundary walls of the pressure swirl nozzle and the shielding air duct at the injector outlet are designed such that the shielding air and the liquid fuel exit the injector under approximately parallel flow directions.
  • a further embodiment provides for the shielding air to emerge from the injector at an angle of attack relative to the direction of flow of the liquid fuel, so that shear forces are exerted on the emerging liquid fuel by the shielding air. This can be achieved by suitable shaping of the outlet opening for the shielding air, in particular the outer sheath delimiting the shielding air duct. The resulting shear rate can improve the atomization result when the liquid fuel is discharged. Particularly high shear rates between the shielding air and the liquid fuel can be achieved with shielding air emerging almost perpendicular to the direction of flow of the liquid fuel.
  • this shift preferably takes place as a function of the combustion air temperature and thus the load of the gas turbine.
  • the screen air speed can be reduced by a suitable shift and thus the atomization, especially the spray angle and the spray quality, can be changed.
  • the last-mentioned embodiments can be implemented both with and without swirl generator in the screen air duct. If a swirl generator is used in the screen air duct, the swirl angle or swirl direction can also have an additional influence on the atomization quality of the liquid fuel.
  • the proposed staged premix burner has such an injector at the tip of a central support for a pilot stage.
  • This central carrier can be designed, for example, in the form of a fuel lance.
  • the premix burner is designed so that the largest possible injector, ie an injector with the largest possible widened cross section, can be used on the nozzle-internal swirl generator. Due to the graduated fuel injection, an injection of - 8 - B03 / 207 -0 SF
  • gaseous fuel at the top of the carrier can be dispensed with as a pilot stage. Rather, such piloting with gaseous fuel is achieved through the staged fuel injection.
  • the premix burner has at least two different groups of fuel outlet openings with separate feeds for the gradual introduction of the gaseous fuel into the combustion air flow.
  • one of these groups of fuel outlet openings can be formed in a part of the carrier located upstream of the injector. This group of fuel outlet openings then forms the pilot stage for gaseous fuel.
  • the different groups of fuel outlet openings for the staged supply of gaseous fuel can also be arranged elsewhere.
  • This relates, for example, to an embodiment of the premix burner in which the swirl generator is formed by a plurality of partial shells which enclose a premixing chamber in the shape of a cone and between which air inlet slots are formed. All or at least part of the fuel outlet openings for the tiered
  • the supply of gaseous fuel is formed in the area of the air inlet openings.
  • the present premix burner enables operation with a reduced pressure drop on the fuel side during spray formation and, in some configurations, additionally improved spray formation.
  • Fig. 1 schematically shows an example of a premix burner according to the prior art
  • FIG. 3 shows a first example of an embodiment of the injector
  • Fig. 5 shows a third example of an embodiment of the injector.
  • this premix burner has a swirl generator 1, which is composed of two partial shells which enclose a premixing chamber in the shape of a cone.
  • Air inlet slots 2 are formed between the two partial shells, which are indicated in the right-hand part of the figure in plan view (viewing direction against the flow direction) of the premix burner.
  • fuel outlet openings 10 for gaseous fuel are arranged, which are supplied with this fuel via corresponding feeds.
  • the introduction of the gaseous fuel into the combustion air stream entering tangentially through the air inlet slots 2 results in a “mixing of the gaseous fuel with the combustion air, promoted by the swirl of the combustion air.
  • a group of fuel outlet openings 10 for gaseous fuel is formed in the half of the burner near the combustion chamber, which forms one of two burner stages in the present case.
  • a second group of fuel outlet openings 9 for gaseous fuel is arranged in the central fuel lance 3 upstream of the tip of this lance 3. This further stage for the supply of gaseous fuel can serve as a pilot stage during the start-up phase of the gas turbine, in whose combustion chamber this burner is used.
  • the first-mentioned burner stage can be divided as desired into different stages which can be acted upon independently of one another with gaseous fuel. These burner stages can of course also extend over the entire axial length of the swirl generator 1.
  • the present injector 4 is arranged at the tip of the fuel lance 3 and can be seen in plan view in the right part of FIG. 2.
  • the figure shows the central outlet nozzle 6 for the liquid fuel ⁇ a and the annular outlet nozzle 5 surrounding it for the shielding air 5a.
  • the staged design of this premix burner prevents the attachment of an additional nozzle for gaseous fuel at the tip of the lance, so that more space is available for the injector for liquid fuel. This very advantageously enables the proposed injector to be used with the widened flow cross section in the region of the swirl generator inside the nozzle.
  • 3 to 5 show exemplary configurations of injectors 4, as can be used in a premix burner according to FIG. 2.
  • 3 is the geometric shape - 12 - B03 / 207-0 SF
  • the swirl nozzle 14 can be clearly seen.
  • This swirl nozzle 14 is locally greatly enlarged in the flow cross section in the region of the swirl grille 12 inside the nozzle.
  • the swirl grid is formed around a central swirl body 15. Due to the more favorable space in the tip of the lance compared to conventional injectors, a larger nozzle can be installed, which significantly reduces the pressure loss, so that this injector can be operated with reduced admission pressure and high atomization capacity.
  • the screen air channel 11 surrounds the swirl nozzle 14. In this application example, the screen air 5a emerges from the lance tip in the axial direction. This is achieved by the geometric design of the limits of the shielding air duct 11 at the outlet end, which are parallel to the axial direction.
  • An additional swirl grille 13 with swirl in the same or opposite direction in relation to the nozzle-internal swirl grille 12 can optionally be arranged in the screen air duct 11.
  • the atomization quality of the liquid fuel as it emerges from the injector can be influenced by adjusting the swirl angle.
  • FIG. 4 shows a further example of the present injector 4, in which it is constructed similarly to that of FIG. 3.
  • the injector 4 shown in FIG. 4 has different exit directions for the screen air 5a and the liquid fuel 6a. Due to the inward configuration of the outlet of the shielding air duct 11, the shielding air flow is adjusted in relation to the direction of flow of the liquid fuel ⁇ a when it exits the injector. in the - 13 - B03 / 207-0 SF
  • a flow field of the screen air is forced almost perpendicular to the flow direction of the liquid fuel by the illustrated embodiment, so that a high shear rate is generated between the screen air and the liquid fuel.
  • This high shear rate promotes the atomization effect.
  • a swirl grille 13 can be arranged in the screen air duct, which, particularly when generating an opposing swirl, can intensify the effect of the atomization.
  • FIG. 5 shows a further example of an injector 4, which is designed comparable to the injector of FIG. 4.
  • the shielding air duct 11 has a variable geometry, which is achieved by the outer casing 16 being able to be moved relative to one another in relation to the swirl nozzle 14 in the axial direction. This displaceability is indicated in the figure by the double arrows. If the swirl nozzle 14 is displaced in relation to the outer casing 16, the outlet gap for the shielding air opens or closes. The shift is preferably carried out as a function of the combustion temperature and thus the load of the gas turbine. For example, in the upper load range, this injector can be used to reduce the screen air speed by increasing the screen air gap and thus changing the spray angle and spray quality.
  • Fuels or fuel emulsions possible in a gas turbine combustion chamber This is made possible above all by the combination of a gas-stage gas turbine burner on the gas side, which enables the injector, which is larger due to the local widening of the swirl nozzle, to be installed in the lance tip.
  • the different designs of the injector can influence the atomization or spray behavior to optimize the respective applications.

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)
  • Spray-Type Burners (AREA)

Abstract

Injecteur (4) pour carburant liquide (6a) et brûleur à prémélange, en particulier pour chambres de combustion de turbines à gaz, possédant un injecteur (4) de ce type. Ledit injecteur (4) comporte une buse à turbulence (14) qui est entourée d'un canal à air de protection (11) et qui possède, dans la zone d'un générateur de turbulences (12), situé dans la buse, pour le carburant liquide (6a), une section transversale d'écoulement agrandie qui se rétrécit à nouveau vers un orifice d'évacuation de la buse à turbulence (14). L'injecteur selon la présente invention permet de faire fonctionner le brûleur à prémélange avec une pression d'admission réduite, pour une excellente qualité d'atomisation.
EP05749973.3A 2004-06-07 2005-06-03 Brûleur étagé à prémélange comprenant in injecteur de carburant liquide Active EP1754002B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004027702A DE102004027702A1 (de) 2004-06-07 2004-06-07 Injektor für Flüssigbrennstoff sowie gestufter Vormischbrenner mit diesem Injektor
PCT/EP2005/052563 WO2005121649A2 (fr) 2004-06-07 2005-06-03 Injecteur pour carburant liquide et bruleur a premelange etage pourvu dudit injecteur

Publications (2)

Publication Number Publication Date
EP1754002A2 true EP1754002A2 (fr) 2007-02-21
EP1754002B1 EP1754002B1 (fr) 2016-03-16

Family

ID=34969534

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05749973.3A Active EP1754002B1 (fr) 2004-06-07 2005-06-03 Brûleur étagé à prémélange comprenant in injecteur de carburant liquide

Country Status (5)

Country Link
US (1) US20070231762A1 (fr)
EP (1) EP1754002B1 (fr)
CN (1) CN1957208B (fr)
DE (1) DE102004027702A1 (fr)
WO (1) WO2005121649A2 (fr)

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EP3361161B1 (fr) * 2017-02-13 2023-06-07 Ansaldo Energia Switzerland AG Ensemble brûleur pour chambre de combustion d'une centrale électrique à turbine à gaz et chambre de combustion comprenant ledit ensemble brûleur
EP3361159B1 (fr) 2017-02-13 2019-09-18 Ansaldo Energia Switzerland AG Procédé de fabrication d'un ensemble brûleur pour une chambre de combustion de turbine à gaz et ensemble brûleur pour une chambre de combustion de turbine à gaz
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Also Published As

Publication number Publication date
CN1957208B (zh) 2010-12-15
DE102004027702A1 (de) 2006-01-05
WO2005121649A3 (fr) 2006-09-14
US20070231762A1 (en) 2007-10-04
WO2005121649A2 (fr) 2005-12-22
EP1754002B1 (fr) 2016-03-16
CN1957208A (zh) 2007-05-02

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