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EP1754002A2 - Injector for liquid fuels and sequential premix burner comprising said injector - Google Patents

Injector for liquid fuels and sequential premix burner comprising said injector

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)
French (fr)
Other versions
EP1754002B1 (en
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/en
Application granted granted Critical
Publication of EP1754002B1 publication Critical patent/EP1754002B1/en
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
    • 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

The invention relates to an injector (4) for liquid fuels (6a) and a premix burner, especially for combustion chambers of gas turbines, comprising such an injector (4). The injector (4) comprises a swirl nozzle (14), surrounded by a shielding air channel (11) and having an enlarged cross-section of flow in the area of a nozzle-internal swirl generator (12) for the liquid fuel (6a), which decreases towards an outlet opening of the swirl nozzle (14). The inventive injector allows operation of a premix burner at reduced admission pressure and excellent quality of atomization.

Description

Injektor für Flüssigbrennstoff sowie gestufter Vor ischbrenner mit diesem Injektor Liquid fuel injector and staged pre-burner with this injector
Technisches AnwendungsgebietTechnical application area
Die vorliegende Erfindung betrifft einen Injektor für Flüssigbrennstoff mit einer Dralldüse zur Eindüsung des Flüssigbrennstoffs, die von einem Schirmluftkanal umgeben ist. Die Erfindung betrifft weiterhin einen gestuften Vormischbrenner, insbesondere für eine Brennkammer einer Gasturbine, mit einem Drallerzeuger für einen Verbrennungsluftstrom, Brennstoff-Austritts- Öffnungen zum gestuften Einbringen von gasförmigem Brennstoff in den Verbrennungsluftstrom und einem zentralen Träger, der einen Injektor mit einer Dralldüse zur Eindüsung von Flüssigbrennstoff sowie einen Schirmluftkanal aufweist.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.
In Gasturbinenanlagen kommen häufig Vormischbrenner zum Einsatz, in denen einströmende Verbrennungsluft mit einem Drall beaufschlagt und durch Eindüsung von Brennstoff in einen Vormischbereich mit dem Brennstoff vermischt wird. Die Vormischbrenner müssen beim Einsatz in Gasturbinen den kompletten Betriebsbereich mit ausreichender Sicherheit abdecken. Dieser Betriebsbereich umfasst beispielsweise auch das Anfahren der Gasturbine, bei dem beim Zünden des Brenners ein Brennstoff/Luft-Gemisch bei Verbrennungsdrücken und Vorwärmtemperaturen nahe den Umgebungs- bedingungen verbrannt werden muss. Zur Sicherstellung der Stabilität des Brennerbetriebes wird der Brenner in - 2 - B03/207-0 SFPremix 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. 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
diesem Betriebsbereich in der Regel mit einer Pilotstufe betrieben. Diese Pilotstufe ist aus Gründen der Symmetrie zentral im BrennerStrömungsfeld, beispielsweise in Form einer Brennstofflanze, angeordnet. Der Brennstoff wird der Verbrennungsluft dabei axial in Strömungsrichtung an der Spitze der Brennstofflanze über einen Injektor so zugegeben, dass brennstoffreiche Zonen im Strömungsfeld des Brenners vorliegen und somit ein stabiler Betrieb ohne Verlöschen der Flamme auch bei niedrigen Verbrennungs- drücken und -temperaturen gewährleistet ist. Bei höherer Betriebslast wird die Eindüsung von Brennstoff über die Pilotstufe zur Schadstoffreduzierung in der Regel verringert und der Brenner im vorteilhaften Vormischbetrieb betrieben.this operating area is usually operated with a pilot stage. For reasons of symmetry, 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. At higher operating loads, the injection of fuel is generally reduced via the pilot stage for reducing pollutants and the burner is operated in advantageous premix mode.
Eine weitere Anforderung an Vormischbrenner sowie alle anderen modernen Gasturbinenbrenner besteht darin, dass der Brenner wahlweise für gasförmige und flüssige Brennstoffe verwendbar sein soll. Dies erfordert eine weitere Anordnung zur BrennstoffInjektion, die in der Regel ebenfalls an der Spitze der Brennstofflanze angebracht ist. Zur Vermeidung von brennstoffhaltigen gasförmigen Rückströmungen in die BrennstoffZuführungen zur Brennstofflanze weist der Brennstoffinjektor an der Brennstofflanze einen Ringspalt auf, aus dem ein, bezogen auf den Gesamtbrennerluftstrom geringer Anteil an Luft ausströmt. Diese so genannte Schirmluft schirmt die beiden Brennstoffdüsen für flüssigen und gas- förmigen Brennstoff gegen unerwünschte Rückströmungen ab. - 3 - B03/207-0 SFAnother requirement for premix burners and all other modern gas turbine burners is that the burner should be usable either for gaseous and liquid fuels. This requires a further arrangement for fuel injection, which is usually also attached to the tip of the fuel lance. To avoid gaseous backflows containing fuel in the fuel feeds to the fuel lance, 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. - 3 - B03 / 207-0 SF
Ein Beispiel für eine Ausgestaltung eines derartigen bekannten Vormischbrenners ist in Fig. 1 in Seitenansicht (links) und Draufsicht (rechts) stark schematisiert dargestellt. Der Drallerzeuger 1 ist in diesem Beispiel aus zwei Teilschalen gebildet, die zu einem kegelmantelförmigen Drallkörper zusammengesetzt sind. Zwischen den beiden Teilschalen liegen Lufteintrittsschlitze 2 für den tangentialen Eintritt von Verbrennungsluft, die in der Figur mit den an dieser Stelle erkennbaren Pfeilen angedeutet sind. Im Vormischbetrieb wird entlang dieserAn 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). In this example, 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
Lufteintrittsschlitze über nicht erkennbare Zuführungen und Brennstoff-Austrittsöffnungen gasförmiger Brennstoff in die Verbrennungsluft eingebracht, um sich innerhalb des durch den Drallerzeuger 1 vorgegebenen Volumens mit der Verbrennungsluft zu vermischen. Innerhalb des Brenners ist zentral eine Brennstofflanze 3 zu erkennen, an deren Ende ein Injektor 4 mit Düsenöffnungen für die Eindüsung von, flüssigem Brennstoff, von gasförmigem Brennstoff sowie für den Austritt von Schirmluft angebracht ist. Die Düsenöffnung 7 für die Einbringung von gasförmigem Brennstoff 7a ist hierbei im rechten Teil der Figur im Zentrum der Brennstofflanze 3 zu erkennen. Diese Düsenöffnung 7 ist von einem Spalt 5 für den Austritt von Schirmluft 5a umgeben. Die im vorliegenden Fall ringförmige Düsenöffnung 6 für die Einbringung von flüssigem Brennstoff βa bildet den äußeren Bereich dieses Injektors 4.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 βa forms the outer region of this injector 4.
Im unteren Lastbereich der Gasturbine wird dieser Vormischbrenner ausschließlich mit einer der beiden Pilotstufen betrieben, d. h. durch die Eindüsung von - 4 - B03/207-0 SFIn the lower load range of the gas turbine, this premix burner is operated exclusively with one of the two pilot stages, ie by injecting - 4 - B03 / 207-0 SF
flüssigem Brennstoff 6a oder von gasförmigem Brennstoff 7a über den Injektor 4 der Brennstofflanze 3. Im oberen Lastbereich muss bei gasförmigen Brennstoffen aufgrund des hohen Schadstoffausstoßes im Pilotbetrieb vollständig auf die Vormischstufe umgeschaltet werden. Bei der Verbrennung flüssiger Brennstoffe in der Pilotstufe wird im oberen Lastbereich eine Emulsion aus Wasser und Öl als Flüssigbrennstoff verbrannt. Durch die Einbringung des Wassers wird lokal im Strömungsfeld die Flammentemperatur abgesenkt. Dies führt zur Senkung der Schadstoffemissionen, insbesondere der Stickoxidemissionen. Neben den Schadstoffemissionen sind im oberen Lastbereich auch Verbrennungspulsationen zu vermeiden, die zu Einschränkungen im Betriebsbereich führen können. Besonders stabil brennende Öl/Wasser- Emulsionsflammen werden hierbei mit Drallinjektoren, auch als Druckdrallinjektoren bezeichnet, erzeugt. Aufgrund des hohen Durchsatzes sowie des beschränkten Platzangebotes im Bereich der Spitze der Brennstoff- lanze rufen derartige Drallinjektoren jedoch einen hohen brennstoffseitigen Druckverlust hervor.liquid fuel 6a or gaseous fuel 7a via the injector 4 of the fuel lance 3. In 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. When burning liquid fuels in the pilot stage, an emulsion of water and oil is burned as a liquid fuel in the upper load range. By introducing the water, the flame temperature is lowered locally in the flow field. This leads to a reduction in pollutant emissions, especially nitrogen oxide emissions. In addition to pollutant emissions, combustion pulsations must also be avoided in the upper load range, which can lead to restrictions in the operating range. Particularly stable burning oil / water emulsion flames are generated with 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.
Darstellung der ErfindungPresentation of the invention
Die Aufgabe der vorliegenden Erfindung besteht darin, einen Injektor für Flüssigbrennstoff sowie einen Vormischbrenner mit einem derartigen Injektor anzugeben, die eine gute Zerstäubungsqualität bei niedrigem Vordruck des Flüssigbrennstoffes erzielen.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.
Die Aufgabe wird mit dem Injektor sowie dem Vormischbrenner gemäß den Patentansprüchen 1 bzw. 10 - 5 - B03/207-0 SFThe object is achieved with the injector and the premix burner in accordance with patent claims 1 and 10, respectively - 5 - B03 / 207-0 SF
gelöst. Vorteilhafte Ausgestaltungen des Injektors sowie des Vor ischbrenners sind Gegenstand der Unteransprüche oder lassen sich der nachfolgenden Beschreibung sowie den Ausführungsbeispielen entnehmen.solved. Advantageous configurations of the injector and the front burner are the subject of the subclaims or can be found in the following description and the exemplary embodiments.
Der vorliegende Injektor für Flüssigbrennstoff umfasst eine Dralldüse zur Eindüsung des Flüssigbrennstoffs sowie einen die Dralldüse umgebenden Schirmluftkanal. Unter Flüssigbrennstoff ist in diesem Zusammenhang nicht nur reiner Brennstoff, wie beispielsweise Öl, sondern auch eine Mischung oder Emulsion dieses Brennstoffes mit anderen Stoffen, insbesondere eine Öl/Wasser-Emulsion, zu verstehen. Die Dralldüse weist einen internen Drallerzeuger für den durchströmenden Flüssigbrennstoff auf und verbreitert sich im Bereich des Drallerzeugers auf einen vergrößerten Strömungsquerschnitt, der sich zur Austrittsöffnung der Dralldüse hin wieder reduziert. Durch die gasseitig gestufte Lanze verbleibt gegenüber herkömmlichen Injektoren mehr Raum für eine grössere Düse, wodurch der Druckverlust reduziert werden kann. Dies ermöglicht den Betrieb dieses Injektors mit niedrigem Vordruck bei dennoch guter Zerstäubungsqualität.The present injector for liquid fuel comprises a swirl nozzle for injecting the liquid fuel and an umbrella air duct surrounding the swirl nozzle. In this context, 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.
Der düseninterne Drallerzeuger ist vorzugsweise als Drallgitter ausgebildet, das sich beispielsweise um einen zentralen Drallkörper innerhalb der Düse erstrecken kann. Weiterhin ist es von Vorteil, innerhalb des die Dralldüse umgebenden Schirmluftkanals ebenfalls einen Drallerzeuger anzuordnen. Die beiden Drallerzeuger können hierbei sowohl gleichsinnigen als auch gegensinnigen Drall erzeugen. Die Erzeugung eines - 6 - B03/207-0 SFThe 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
gegenüber dem düseninternen Drallerzeuger gegensinnigen Dralls der Schirmluft kann einen positiven Einfluss auf die Zerstäubungsqualität des austretenden Flüssigbrennstoffes haben. Die Stärke und Richtung des Dralls lässt sich zur Erzeugung einer für die jeweiligeopposite 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
Anwendung optimalen Eindüsung des Flüssigbrennstoffs über die geometrische Ausgestaltung des Drallerzeugers optimieren. In einer Ausgestaltung des Injektors ist derOptimize the application of the optimal injection of the liquid fuel via the geometric design of the swirl generator. In one embodiment of the injector
Austrittsbereich, d.h. insbesondere die Begrenzungswände der Druckdralldüse und des Schirmluftkanals am Injektoraustritt, so ausgebildet, dass die Schirmluft und der Flüssigbrennstoff unter annähernd parallelen Strömungsrichtungen aus dem Injektor austreten. Eine weitere Ausgestaltung sieht vor, die Schirmluft unter einem Anstellwinkel zur Strömungsrichtung des Flüssigbrennstoffs aus dem Injektor austreten zu lassen, so dass durch die Schirmluft Scherkräfte auf den austretenden Flüssigbrennstoff ausgeübt werden. Dies lässt sich durch eine geeignete Ausformung der Austrittsöffnung für die Schirmluft, insbesondere der den Schirmluftkanal begrenzenden äußeren Ummantelung erreichen. Durch die dadurch erzeugte Scherrate lässt sich das Zerstäubungsergebnis beim Austritt des Flüssigbrennstoffs verbessern. Besonders hohe Scherraten zwischen der Schirmluft und dem Flüssigbrennstoff lassen sich mit nahezu senkrecht zur Strömungsrichtung des Flüssigbrennstoffes austretender Schirmluft erreichen.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.
In einer weiteren vorteilhaften Ausgestaltung des Injektors sind die Dralldüse und die diese umgebende - 7 - B03/207-0 SFIn a further advantageous embodiment of the injector, the swirl nozzle and the one surrounding it - 7 - B03 / 207-0 SF
äußere Um antelung, die zusammen mit der Dralldüse den Schirmluftkanal bildet, in axialer Richtung, d.h. in Hauptströmungsrichtung des Flüssigbrennstoffs, gegeneinander verschiebbar angeordnet. Dies ermöglicht die Variation der geometrischen Form der Austrittsöffnung der Schirmluft durch die gegenseitige Verschiebung. Beim Einsatz in einem Vormischbrenner einer Gasturbinenbrennkammer erfolgt diese Verschiebung vorzugsweise in Abhängigkeit von der Verbrennungsluft- temperatur und damit der Last der Gasturbine. Im oberen Lastbereich können durch geeignete Verschiebung die Schirmluftgeschwindigkeit reduziert und somit die Zerstäubung, vor allem der Spraywinkel und die Sprayqualität, geändert werden.outer encircling, which together with the swirl nozzle forms the screen air duct, in the axial direction, i.e. arranged in the main flow direction of the liquid fuel, displaceable against each other. This enables the geometric shape of the outlet opening of the screen air to be varied by the mutual displacement. When used in a premix burner of a gas turbine combustion chamber, this shift preferably takes place as a function of the combustion air temperature and thus the load of the gas turbine. In the upper load range, 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.
Selbstverständlich lassen sich die letztgenannten Ausführungsformen sowohl mit als auch ohne Drallerzeuger im Schirmluftkanal realisieren. Bei Einsatz eines Drallerzeugers im Schirmluftkanal kann auch hier über den Drallwinkel bzw. die Drallrichtung zusätzlich Einfluss auf die Zerstäubungsqualität des Flüssigbrennstoffes ausgeübt werden.Of course, 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.
Der vorgeschlagene gestufte Vormischbrenner weist einen derartigen Injektor an der Spitze eines zentralen Trägers für eine Pilotstufe auf. Dieser zentrale Träger kann beispielsweise in Form einer Brennstofflanze ausgebildet sein. Der Vormischbrenner ist dabei konstruktiv so ausgelegt, dass ein möglichst großer Injektor, d.h. ein Injektor mit einem möglichst großen verbreiterten Querschnitt am düseninternen Drallerzeuger, eingesetzt werden kann. Durch die gestufte Brennstoffeindüsung kann auf eine Injektion von - 8 - B03/207 -0 SFThe 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
gasförmigem Brennstoff an der Spitze des Trägers als Pilotstufe verzichtet werden. Vielmehr wird eine derartige Pilotierung mit gasförmigem Brennstoff durch die gestufte Brennstoffeindüsung erreicht. Der Vormischbrenner weist hierzu zumindest zwei unterschiedliche Gruppen von Brennstoff-Austrittsöffnungen mit getrennten Zuführungen zum gestuften Einbringen des gasförmigen Brennstoffs in den Verbrennungsluftstrom auf. In einer Ausgestaltung des Vormischbrenners kann eine dieser Gruppen von Brennstoff-Austrittsöffnungen in einem stromauf des Injektors liegenden Teil des Trägers ausgebildet sein. Diese Gruppe von Brennstoff-Austrittsöffnungen bildet dann die Pilotstufe für gasförmigen Brennstoff.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. For this purpose, 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. In one embodiment of the premix burner, 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.
Selbstverständlich lassen sich die unterschiedlichen Gruppen von Brennstoff-AustrittsÖffnungen für die gestufte Zuführung von gasförmigem Brennstoff auch an anderer Stelle anordnen. Dies betrifft beispiels- weise eine Ausgestaltung des Vormischbrenners, bei der der Drallerzeuger durch mehrere Teilschalen gebildet ist, die einen Vormischraum kegelmantelförmig umschließen und zwischen denen Lufteintrittsschlitze ausgebildet sind. Alle oder zumindest ein Teil der Brennstoff-Austrittsöffnungen für die gestufteOf course, 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
Zuführung von gasförmigem Brennstoff ist dabei im Bereich der Lufteintrittsöffnungen ausgebildet.The supply of gaseous fuel is formed in the area of the air inlet openings.
Der vorliegende Vormischbrenner ermöglicht aufgrund des speziellen Injektors einen Betrieb mit einem verringerten brennstoffseitigen Druckverlust bei der Spraybildung sowie bei einigen Ausgestaltungen eine zusätzlich verbesserte Spraybildung. - 9 - B03/207-0 SFDue to the special injector, 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. - 9 - B03 / 207-0 SF
Kurze Beschreibung der Zeichnungen Der vorliegende Injektor sowie der Vormischbrenner mit diesem Injektor werden nachfolgend anhand von Ausführungsbeispielen in Verbindung mit den Zeichnungen nochmals näher erläutert. Hierbei zeigen:BRIEF DESCRIPTION OF THE DRAWINGS The present injector and the premix burner with this injector are explained in more detail below on the basis of exemplary embodiments in conjunction with the drawings. Here show:
Fig .1 schematisch ein Beispiel für einen Vormischbrenner gemäß dem Stand der Technik;Fig. 1 schematically shows an example of a premix burner according to the prior art;
Fig. 2 schematisch ein Beispiel für eine Ausgestaltung eines Vormischbrenners mit dem vorliegenden Injektor;2 schematically shows an example of an embodiment of a premix burner with the present injector;
Fig. 3 ein erstes Beispiel für eine Ausgestaltung des Injektors;3 shows a first example of an embodiment of the injector;
Fig. 4 ein zweites Beispiel für eine Ausgestaltung des Injektors; und4 shows a second example of an embodiment of the injector; and
Fig. 5 ein drittes Beispiel für eine Ausgestaltung des Injektors.Fig. 5 shows a third example of an embodiment of the injector.
Wege zur Ausführung der ErfindungWays of Carrying Out the Invention
Der Aufbau eines Vormischbrenners gemäß dem Stand der Technik, wie er in der Fig. 1 schematisch dargestellt ist, wurde bereits in der Beschreibungseinleitung eingehend erläutert. - 10 - B03/207-0 SFThe structure of a premix burner according to the prior art, as shown schematically in FIG. 1, was already explained in detail in the introduction to the description. - 10 - B03 / 207-0 SF
Fig. 2 zeigt nun schematisch ein Beispiel für eine Ausgestaltung des vorliegenden gestuften Vormischbrenners, bei dem der erfindungsgemäße Injektor zum Einsatz kommt. Dieser Vormischbrenner weist in bekannter Weise einen Drallerzeuger 1 auf, der aus zwei Teilschalen zusammengesetzt ist, die kegelmantelförmig einen Vormischraum umschließen. Zwischen den beiden Teilschalen sind Lufteintrittsschlitze 2 ausgebildet, die im rechten Teil der Figur in Draufsicht (Blickrichtung entgegen der Strömungsrichtung) auf den Vormischbrenner angedeutet sind. Im Bereich dieser Lufteintrittsschlitze 2 sind Brennstoff-Austrittsöffnungen 10 für gasförmigen Brennstoff angeordnet, die über entsprechende Zuführungen mit diesem Brennstoff beaufschlagt werden. Durch das Einbringen des gasförmigen Brennstoffes in den tangential durch die Lufteintrittsschlitze 2 eintretenden Verbrennungsluftstrom erfolgt eine durch den Drall der Verbrennungsluft geförderte „Vermischung des gasförmigen Brennstoffes mit der Verbrennungsluft.2 now schematically shows an example of an embodiment of the present staged premix burner, in which the injector according to the invention is used. In a known manner, 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. In the area of these air inlet slots 2, 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.
Im vorliegenden Beispiel ist eine Gruppe von Brennstoff-Austrittsöffnungen 10 für gasförmigen Brennstoff in der brennraumnahen Hälfte des Brenners ausgebildet, die eine von im vorliegenden Fall zwei Brennerstufen bildet . Eine zweite Gruppe von Brennstoff-Austrittsöffnungen 9 für gasförmigen Brennstoff ist in der zentralen Brennstofflanze 3 stromauf der Spitze dieser Lanze 3 angeordnet. Diese weitere Stufe für die Zuführung gasförmigen Brennstoffs kann während der Anfahrphase der Gasturbine, in deren Brennkammer dieser Brenner eingesetzt wird, als Pilotstufe dienen. Selbstverständlich kann auch die - 11 - B03/207-0 SFIn the present example, 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. Of course, the - 11 - B03 / 207-0 SF
erstgenannte Brennerstufe beliebig in unterschiedliche Stufen aufgeteilt werden, die unabhängig voneinander mit gasförmigem Brennstoff beaufschlagbar sind. Diese Brennerstufen können sich selbstverständlich auch über die gesamte axiale Länge des Drallerzeugers 1 erstrecken.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.
An der Spitze der Brennstofflanze 3 ist der vorliegende Injektor 4 angeordnet, der im rechten Teil der Figur 2 in Draufsicht zu erkennen ist. Die Figur zeigt hierbei die zentrale Austrittsdüse 6 für den Flüssigbrennstoff βa sowie die diesen umgebende ringförmige Austrittsdüse 5 für die Schirmluft 5a. Durch die gestufte Ausbildung dieses Vormischbrenners wird die Anbringung einer zusätzlichen Düse für gasförmigen Brennstoff an der Lanzenspitze vermieden, so dass mehr Platz für den Injektor für Flüssig- brennstoff zur Verfügung steht. Dies ermöglicht sehr vorteilhaft den Einsatz des vorgeschlagenen Injektors mit dem verbreiterten Strömungsquerschnitt im Bereich des düseninternen Drallerzeugers.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 βa 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.
Im Anfahrbetrieb der Gasturbine wird ein Großteil des Brennstoffes über die Brennstofflanze 3 zugegeben. Erst bei höherer Last wird der Brenner mit niedrigeren Brennstoffanteilen über die Lanzenstufe betrieben, die eine Optimierung des Pulsations- und Schadstoffemissionsverhaltens ermöglichen. Die Fig. 3 bis 5 zeigen beispielhafte Ausgestaltungen von Injektoren 4, wie sie bei einem Vormischbrenner gemäß Fig. 2 eingesetzt werden können. Bei der Ausgestaltung gemäss Fig. 3 ist die geometrische Form - 12 - B03/207-0 SFWhen the gas turbine is started up, a large part of the fuel is added via the fuel lance 3. Only when the load is higher is the burner operated with lower fuel proportions via the lance stage, which enable the pulsation and pollutant emission behavior to be optimized. 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
der Dralldüse 14 gut zu erkennen. Diese Dralldüse 14 ist im Bereich des düseninternen Drallgitters 12 im Strömungsquerschnitt lokal stark vergrößert. Das Drallgitter ist hierbei um einen zentralen Drallkörper 15 ausgebildet. Aufgrund der gegenüber herkömmlichen Injektoren günstigeren Platzverhältnisse in der Lanzenspitze kann eine grössere Düse eingebaut werden, wodurch sich der Druckverlust deutlich vermindert, so dass dieser Injektor mit verringertem Vordruck bei hoher Zerstäubungsleistung betrieben werden kann. Der Schirmluftkanal 11 umgibt die Dralldüse 14. Die Schirmluft 5a tritt in diesem Anwendungsbeispiel in axialer Richtung aus der Lanzenspitze aus . Dies wird durch die geometrische Ausbildung der Begrenzungen des Schirmluftkanals 11 am Austrittsende erreicht, die parallel zur axialen Richtung verlaufen. Im Schirmluftkanal 11 kann wahlweise ein zusätzliches Drallgitter 13 mit im Verhältnis zum düseninternen Drallgitter 12 gleich- oder gegensinnigem Drall angeordnet sein. Über die Einstellung des Drallwinkels kann die Zerstäubungsqualität des Flüssigbrennstoffes beim Austritt aus dem Injektor beeinflusst werden.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 zeigt ein weiteres Beispiel für den vorliegenden Injektor 4, bei dem dieser ähnlich aufgebaut ist, wie der der Fig. 3. Der in der Fig. 4 dargestellte Injektor 4 weist jedoch unterschiedliche Austrittsrichtungen für die Schirmluft 5a und den Flüssigbrennstoff 6a auf. Durch die nach innen gerichtete Ausbildung des Austritts des Schirmluftkanals 11 wird eine Anstellung der Schirmluftströmung gegenüber der Strömungsrichtung des Flüssigbrennstoffes βa beim Austritt aus dem Injektor erreicht. Im - 13 - B03/207-0 SFFIG. 4 shows a further example of the present injector 4, in which it is constructed similarly to that of FIG. 3. However, 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 βa when it exits the injector. in the - 13 - B03 / 207-0 SF
vorliegenden Beispiel wird durch die dargestellte Ausgestaltung ein Strömungsfeld der Schirmluft nahezu senkrecht zur Strömungsrichtung des Flüssigbrennstoffes erzwungen, so dass eine hohe Scherrate zwischen der Schirmluft und dem Flüssigbrennstoff erzeugt wird. Diese hohe Scherrate fördert den Zerstäubungseffekt . Auch hier kann ein Drallgitter 13 im Schirmluftkanal angeordnet sein, das, insbesondere bei der Erzeugung eines gegensinnigen Dralls, den Effekt der Zerstäubung noch verstärken kann.In the present example, 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. Here, too, 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 zeigt schließlich ein weiteres Beispiel eines Injektors 4, der vergleichbar dem Injektor der Fig. 4 ausgebildet ist. Der Schirmluftkanal 11 weist in diesem Beispiel allerdings eine variable Geometrie auf, die durch eine gegenseitige Verschiebbarkeit der äußeren Ummantelung 16 gegenüber der Dralldüse 14 in axialer Richtung erreicht wird. Diese Verschiebbarkeit ist in der Figur durch, die Doppelpfeile angedeutet. Wird die Dralldüse 14 gegenüber der äußeren Ummantelung 16 verschoben, so öffnet oder schließt sich der Austrittsspalt für die Schirmluft. Die Verschiebung wird vorzugsweise in Abhängigkeit von der Verbrennungstemperatur und damit der Last der Gasturbine vorge- nommen. So können beispielsweise im oberen Lastbereich mit Hilfe dieses Injektors durch Vergrößerung des Schirmluftspaltes die Schirmluftgeschwindigkeit reduziert und somit der Spraywinkel und die Sprayqualität geändert werden.Finally, FIG. 5 shows a further example of an injector 4, which is designed comparable to the injector of FIG. 4. In this example, however, 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.
Durch die vorliegende Ausgestaltung des Injektors bzw. Vormischbrenners ist ein Schadstoffarmer und pulsationsfreier Betrieb bei der Verbrennung flüssiger - 14 - B03/207-0 SFDue to the present design of the injector or premix burner, low-pollutant and pulsation-free operation is more liquid during combustion - 14 - B03 / 207-0 SF
Brennstoffe oder Brennstoffemulsionen in einer Gasturbinenbrennkammer möglich. Dies wird vor allem durch die Kombination eines gasseitig brennstoffgestuften Gasturbinenbrenners ermöglicht, der den Einbau des durch lokale Verbreiterung der Dralldüse größeren Injektors in der Lanzenspitze ermöglicht. Durch die unterschiedlichen Ausgestaltungen des Injektors lässt sich das Zerstäubungs- bzw. Sprayverhalten zur Optimierung der jeweiligen Anwendungen beeinflussen. 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.
15 - B03/207-0 SF15 - B03 / 207-0 SF
BEZÜGSZEICHEN I STEREFERENCE SIGN I STE

Claims

- 16 - B03/207-0 SF - 16 - B03 / 207-0 SF
Patentansprücheclaims
1. Injektor für Flüssigbrennstoff, insbesondere für einen Vormischbrenner, mit einer Dralldüse (14) zur Eindüsung des Flüssigbrennstoffs (6a) , die von einem Schirmluftkanal (11) für Schirmluft (5a) umgeben ist und im Bereich eines düseninternen Drallerzeugers (12) für den Flüssigbrennstoff (6a) einen vergrößerten Strömungsquerschnitt aufweist, der sich zu einer Austrittsöffnung der Dralldüse (14) wieder reduziert.1. Injector for liquid fuel, in particular for a premix burner, with a swirl nozzle (14) for injecting the liquid fuel (6a), which is surrounded by a shielding air duct (11) for shielding air (5a) and in the area of a swirl generator (12) inside the nozzle for the Liquid fuel (6a) has an enlarged flow cross section, which reduces again to an outlet opening of the swirl nozzle (14).
2. Injektor nach Anspruch 1, dadurch gekennzeichnet, dass der düseninterne Drallerzeuger (12) als Drallgitter ausgebildet ist.2. Injector according to claim 1, characterized in that the nozzle-internal swirl generator (12) is designed as a swirl grille.
3. Injektor nach Anspruch 2, dadurch gekennzeichnet, dass sich das Drallgitter um einen zentralen Drallkörper (15) erstreckt.3. Injector according to claim 2, characterized in that the swirl grid extends around a central swirl body (15).
4. Injektor nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass im Schirmluftkanal (11) ein kanalinterner Drallerzeuger (13) angeordnet ist.4. Injector according to one of claims 1 to 3, characterized in that an internal swirl generator (13) is arranged in the screen air duct (11).
5. Injektor nach Anspruch 4, dadurch gekennzeichnet, dass der kanalinterne Drallerzeuger (13) im Schirmluftkanal (11) und der düseninterne - 17 - B03/207-0 SF5. Injector according to claim 4, characterized in that the channel-internal swirl generator (13) in the screen air channel (11) and the nozzle-internal - 17 - B03 / 207-0 SF
Drallerzeuger (12) so ausgebildet sind, dass sie einen gegensinnigen Drall erzeugen.Swirl generators (12) are designed in such a way that they produce an opposite swirl.
Injektor nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Injektor (4) so ausgebildet ist, dass der Flüssigbrennstoff (6a) und die Schirmluft (5a) mit annähernd parallelen Strömungsrichtungen aus dem Injektor (4) austreten.Injector according to one of claims 1 to 5, characterized in that the injector (4) is designed such that the liquid fuel (6a) and the shielding air (5a) emerge from the injector (4) with approximately parallel flow directions.
7. Injektor nach Anspruch 6, dadurch gekennzeichnet, dass Begrenzungswände der Dralldüse (14) und des Schirmluftkanals (11) an einem Austritt des Injektors (4) annähernd parallel verlaufen.7. Injector according to claim 6, characterized in that boundary walls of the swirl nozzle (14) and the shielding air duct (11) run approximately parallel at an outlet of the injector (4).
8. Injektor nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Schirmluftkanal (11) an einem Austritt des Injektors (4) so ausgebildet ist, dass die Schirmluft (5a) unter einem Anstellwinkel zu einer Austrittsrichtung des Flüssigbrennstoffes (6a) austritt, um Scherkräfte auf den Flüssigbrennstoff (6a) auszuüben.8. Injector according to one of claims 1 to 5, characterized in that the shield air duct (11) is formed at an outlet of the injector (4) so that the shield air (5a) exits at an angle of attack to an outlet direction of the liquid fuel (6a) to exert shear forces on the liquid fuel (6a).
9. Injektor einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass die Dralldüse (14) und eine äußere Ummantelung (16) , die in Verbindung mit der Dralldüse (14) den Schirmluftkanal (11) bildet, in axialer Richtung des Injektors (4) gegenseitig verschiebbar angeordnet sind. - 18 - B03/207-0 SF9. Injector according to one of claims 1 to 8, characterized in that the swirl nozzle (14) and an outer casing (16), which in conjunction with the swirl nozzle (14) forms the screen air duct (11), in the axial direction of the injector (4th ) are arranged to be mutually displaceable. - 18 - B03 / 207-0 SF
10. Gestufter Vormischbrenner, insbesondere für eine Brennkammer einer Gasturbine, mit einem Drallerzeuger (1) für einen Verbrennungsluftström, Brennstoff-Austrittsöffnungen (9, 10) mit Zuführungen zum gestuften Einbringen von gasförmigem Brennstoff in den Verbrennungsluftstrom und einem zentralen Träger (3) , der einen Injektor (4) mit einer Dralldüse (14) zur Eindüsung von Flüssigbrennstoff (6a) und einem Schirmluftkanal (11) für Schirmluft (5a) aufweist, wobei die Dralldüse (14) vom Schirmluftkanal (11) umgeben ist und im Bereich eines düseninternen Drallerzeugers (12) für den Flüssigbrennstoff (6a) einen vergrößerten Strömungsquerschnitt aufweist, der sich zu einer Austrittsöffnung der Dralldüse (14) wieder reduziert.10. Staged premix burner, in particular for a combustion chamber of a gas turbine, with a swirl generator (1) for a combustion air flow, fuel outlet openings (9, 10) with feeds for the gradual introduction of gaseous fuel into the combustion air flow and a central carrier (3), the has an injector (4) with a swirl nozzle (14) for injecting liquid fuel (6a) and a shielding air duct (11) for shielding air (5a), the swirl nozzle (14) being surrounded by the shielding air duct (11) and in the region of a swirl generator internal to the nozzle (12) for the liquid fuel (6a) has an enlarged flow cross section, which is reduced to an outlet opening of the swirl nozzle (14) again.
11. Vormischbrenner Anspruch 10, dadurch gekennzeichnet, dass ein Teil der Brennstoff-Austrittsöffnungen (9) zum Einbringen von gasförmigem Brennstoff in den Verbrennungsluftstrom in einem stromauf des Injektors (4) liegenden Teil des Trägers (3) ausgebildet ist.11. premix burner according to claim 10, characterized in that a part of the fuel outlet openings (9) for introducing gaseous fuel into the combustion air stream is formed in a part of the carrier (3) located upstream of the injector (4).
12. Vormischbrenner Anspruch 10 oder 11, dadurch gekennzeichnet, dass der Drallerzeuger (1) durch mehrere Teilschalen gebildet ist, die einen Vormischraum kegelmantelförmig umschließen und zwischen denen Lufteintrittsschlitze (2) ausgebildet sind. - 19 - B03/207-0 SF12. premix burner according to claim 10 or 11, characterized in that the swirl generator (1) is formed by several partial shells which enclose a premixing chamber in the shape of a cone and between which air inlet slots (2) are formed. - 19 - B03 / 207-0 SF
13. Vormischbrenner nach Anspruch 12, dadurch gekennzeichnet, dass zumindest ein Teil der Brennstoff-Austrittsöffnungen (10) zum Einbringen von gasförmigem Brennstoff in den Verbrennungsluftström im Bereich der Lufteintrittsschlitze (2) am Drallerzeuger (1) angeordnet ist.13. Premix burner according to claim 12, characterized in that at least part of the fuel outlet openings (10) for introducing gaseous fuel into the combustion air flow is arranged in the region of the air inlet slots (2) on the swirl generator (1).
14. Vormischbrenner nach einem der Ansprüche 10 bis 13, dadurch gekennzeichnet, dass der düseninterne Drallerzeuger (12) als Drallgitter ausgebildet ist.14. Premix burner according to one of claims 10 to 13, characterized in that the nozzle-internal swirl generator (12) is designed as a swirl grid.
15. Vormischbrenner nach Anspruch 14, dadurch gekennzeichnet, dass sich das Drallgitter um einen zentralen Drallkörper (15) erstreckt.15. Premix burner according to claim 14, characterized in that the swirl grid extends around a central swirl body (15).
16. Vormischbrenner nach einem der Ansprüche 10 bis 15, dadurch gekennzeichnet, dass im Schirmluftkanal (11) ein kanalinterner Drallerzeuger (13) angeordnet ist.16. Premix burner according to one of claims 10 to 15, characterized in that an internal swirl generator (13) is arranged in the screen air duct (11).
17. Vormischbrenner nach Anspruch 16, dadurch gekennzeichnet, dass der kanalinterne Drallerzeuger (13) im Schirmluftkanal (11) und der düseninterne Drallerzeuger (12) so ausgebildet sind, dass sie einen gegensinnigen Drall erzeugen. - 20 - B03/207-0 SF17. premix burner according to claim 16, characterized in that the channel-internal swirl generator (13) in the shielding air duct (11) and the nozzle-internal swirl generator (12) are designed such that they produce an opposing swirl. - 20 - B03 / 207-0 SF
18. Vormischbrenner nach einem der Ansprüche 10 bis 17, dadurch gekennzeichnet, dass der Injektor (14) so ausgebildet ist, dass der Flüssigbrennstoff (6a) und die Schirmluft (5a) mit annähernd parallelen Strömungsrichtungen in axialer Richtung des Trägers (3) aus dem Injektor (4) austreten.18. premix burner according to one of claims 10 to 17, characterized in that the injector (14) is designed such that the liquid fuel (6a) and the shielding air (5a) with approximately parallel flow directions in the axial direction of the carrier (3) from the Exit injector (4).
19. Vormischbrenner nach Anspruch 18, dadurch gekennzeichnet, dass Begrenzungswände der Dralldüse (14) und des Schirmluftkanals (11) an einem Austritt des Injektors (4) annähernd koaxial verlaufen.19. premix burner according to claim 18, characterized in that boundary walls of the swirl nozzle (14) and the screen air duct (11) at an outlet of the injector (4) extend approximately coaxially.
20. Vormischbrenner nach einem der Ansprüche 10 bis 17, dadurch gekennzeichnet, dass der Schirmluftkanal (11) an einem Austritt des Injektors (4) so ausgebildet ist, dass die Schirmluft (5a) unter einem Anstellwinkel zu einer Austrittsrichtung des Flüssigbrennstoffes (6a) austritt, um Scherkräfte auf den Flüssigbrennstoff (6a) auszuüben.20. premix burner according to one of claims 10 to 17, characterized in that the shield air duct (11) is formed at an outlet of the injector (4) so that the shield air (5a) exits at an angle of attack to an outlet direction of the liquid fuel (6a) to exert shear forces on the liquid fuel (6a).
21. Vormischbrenner einem der Ansprüche 10 bis 20, dadurch gekennzeichnet, dass die Dralldüse (14) und eine äußere Ummantelung (16) , die in Verbindung mit der Dralldüse (14) den Schirmluftkanal (11) bildet, in axialer Richtung des Trägers (3) gegenseitig verschiebbar angeordnet sind. 21. Premix burner according to one of claims 10 to 20, characterized in that the swirl nozzle (14) and an outer casing (16), which in conjunction with the swirl nozzle (14) forms the screen air duct (11), in the axial direction of the carrier (3 ) are arranged to be mutually displaceable.
EP05749973.3A 2004-06-07 2005-06-03 Staged premix burner with an injector for liquid fuel Not-in-force EP1754002B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004027702A DE102004027702A1 (en) 2004-06-07 2004-06-07 Injector for liquid fuel and stepped premix burner with this injector
PCT/EP2005/052563 WO2005121649A2 (en) 2004-06-07 2005-06-03 Injector for liquid fuels and sequential premix burner comprising said injector

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EP1754002A2 true EP1754002A2 (en) 2007-02-21
EP1754002B1 EP1754002B1 (en) 2016-03-16

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US (1) US20070231762A1 (en)
EP (1) EP1754002B1 (en)
CN (1) CN1957208B (en)
DE (1) DE102004027702A1 (en)
WO (1) WO2005121649A2 (en)

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Also Published As

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

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