EP1855054B1 - Method for supplying fuel to a premix burner - Google Patents
Method for supplying fuel to a premix burner Download PDFInfo
- Publication number
- EP1855054B1 EP1855054B1 EP07113855.6A EP07113855A EP1855054B1 EP 1855054 B1 EP1855054 B1 EP 1855054B1 EP 07113855 A EP07113855 A EP 07113855A EP 1855054 B1 EP1855054 B1 EP 1855054B1
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- EP
- European Patent Office
- Prior art keywords
- premix
- burner
- gas
- region
- supply
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- 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.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
Definitions
- the invention relates to a device with a premix burner, a fuel supply and a control unit for operating a gas turbine, wherein the premix burner has at least one burner shell at least partially delimiting an axially extending premixing chamber, with one directed into the premixing chamber via the burner cup Premix gas supply, wherein the premix gas is mixed with combustion air and ignited downstream, outside the premix burner.
- Premix burners of the aforementioned type are well known for operating gas turbine plants and have different premix burner geometries. So is in the EP 0 321 809 B1 a cone-shaped premix burner consisting of several burner shells, a so-called double-cone burner, whose burner shells are composed in such a way that tangential air inlet slots for the combustion air are formed along the burner axis. At the inflow edges of the burner shells formed thereby are provided outlet openings for the premix gas, which are distributed in the direction of the burner axis. The injection of the premix gas through the outlet openings along the inflow edges of the burner shells leads due to the burner shell geometry in conjunction with the combustion air supply to a swirling mixing of the premix gas and the combustion air supply.
- premix burner geometry is in the WO 93/17279 shown, in which the premix burner is formed with an additional conical inner body. Also in this case, the premix gas is fed into the premix burner via respective exit openings arranged along the axially extending air inlet slots, where the premix gas is mixed with combustion air and ignited downstream within the combustion chamber.
- the emission values, the extinguishing behavior of the flame forming in the combustion chamber, the flame backflow behavior and the flame stability can be decisively influenced by a suitable choice of the abovementioned parameters.
- premix burners With the presently known premix burners, it is almost impossible to operate the premix burner with different types of fuel, such as liquid or gaseous fuel, especially as the burner lance generally arranged centrally in the burner axis for supplying pilot gas, as mentioned above, for powering up the gas turbine and for the lower load range is required, is located in close proximity to the central liquid fuel nozzle. Unintended ignition interactions between the two fuel outlets can not be excluded.
- fuel such as liquid or gaseous fuel
- the two writings DE-A1-44 46 945 and EP-A1-0 592 717 disclose gas-powered premix burners in which combustion air is introduced at least approximately tangentially into the pre-mixing chamber of the burner. Fuel is injected via a plurality of nozzles arranged in the longitudinal direction of the premixing chamber and mixed with the combustion air. The nozzles are divided into at least two groups with different fuel supply.
- the invention has the object of providing a device with a premix burner, a fuel supply and a control or regulating unit according to the preamble of claim 1 such that the above-mentioned prior art disadvantages are avoided.
- it is necessary to take measures at the premix burner, so that an optimized adaptation of the premix burner behavior in the entire load range of the gas turbine is possible. This should in particular be done without great technical and design effort and be feasible with only a small cost.
- the idea underlying the invention is the axial stepped supply of premix gas along the flanks of the burner shells by the burner shells are divided into at least two axially successively arranged areas, which are each supplied via PremixgaszuWORKtechnischen separated.
- the separate areas along the burner shells are arranged axially behind one another in the direction of flow of the premix burner, wherein it has been recognized according to the invention that more than 60% of the total premix gas supply is to be made via the upstream first region for starting up the gas turbine and that the load is required for the further startup Gas turbine to full load a gradual or continuous redistribution of Premixgaszu Entry on the downstream of the first area adjacent areas takes place.
- An embodiment designed according to the invention for the targeted supply control of premix gas for the burner shells of the premix burner subdivided into different regions is set out in the following description with reference to the figures.
- An essential aspect of the device described in detail below is the separate, metered premix gas supply to the individual, axially successively arranged regions along the burner shells, through which the premix gas is injected into the interior of the premix burner.
- FIG. 1 is a schematic representation of a longitudinal section through a cone-shaped Vormischbrenner shown.
- the premix burner has cone-shaped burner shells 1, 2 along which premix gas outlet openings 3 are provided in the axial direction of the burner longitudinal axis A, through which premix gas can be fed into the interior of the premix burner.
- the burner shells 1, 2 are divided into two differently separated regions, stage S1 and stage S2, which are supplied with premix gas by different premix gas supply lines 4, 5.
- stage S1 and stage S2 which are supplied with premix gas by different premix gas supply lines 4, 5.
- air inlet slots supply air led into the interior of the premix burner, which mixes with the premix gas 6 to a fuel air mixture.
- a liquid fuel atomization direction 7 can be provided in the center of the premix burner, which allows mixing operation or switching from gaseous fuel to liquid fuel.
- the supply of liquid fuel takes place with the aid of a known atomizing nozzle, which generates a conically spreading atomizing cloud within the premix burner.
- the spreading liquid fuel cloud is surrounded by a protective air jacket.
- a pilot is not, as is common in the prior art, made, but in the illustrated in the embodiment two-stage premix burner each area of the burner shell is supplied with a Premixgaszubow upstream in the premix burner is arranged. In the exemplary embodiment, this is the area stage 1, which is operated for starting and for operating the premix burner in the low load range with more than 60% of the total Premixgaszu exit.
- FIG. 2 An overview diagram emerges from which the percentage distribution of the premix gas distribution between area S1 and area S2 increases can be found.
- the fields entered in black correspond to the portion of the premix gas exiting via region 1, the brighter fields in each case to the premix gas fraction which reaches the interior of the burner via region S2 of the premix burner.
- the lion's share ie, more than 90%
- the proportion of the premix gas emerging over the region S2 increases slightly.
- both areas S1 and S2 are supplied with premix gas in approximately equal parts.
- FIG. 3 Another possibility of controlled premix gas supply to the separate areas of the premix burner is shown in the schematic representation according to FIG. 3 refer to. Again, it is in accordance with the embodiment FIG. 3 around a cone-shaped premix burner, which has two regions S1 and S2, via which premix gas enters the interior of the premix burner separately.
- a main control valve 9 is provided in a common supply line 8 via which premix gas is supplied to the premix burner.
- the direct inflow of premix gas to the area S1 of the premix burner can be regulated.
- a crossing point 10 is provided at which a portion of the premix gas is discharged into a branch line 11.
- a further control unit in the form of a spring-loaded pressure relief valve 12 is provided, which will be described in more detail below with reference to FIG. 4 is described.
- a bypass line 13 whose flow cross-section is small enough or in the a corresponding throttle element 14 is provided, ensures that when the control valve 12 is closed, a small premix gas flow to the region S2 of the premix burner can be supplied.
- the prevailing in the branch line 11 Premixgastik increases, which is able to open the spring-loaded throttle valve 12 continuously, whereby an increasing proportion of flowing through the main control valve 9 premix gas flows through the pressure relief valve 12 into the area S2. If the supply gas pressure continues to increase, the overpressure valve 12 opens completely, as a result of which a large proportion of the premix gas can reach the region S2 of the premix burner.
- the supply lines and adjusting the response of the pressure relief valve 12 it is possible to optimize the behavior of the premix burner in terms of emission and vibration behavior.
- Such a pressure relief valve is as an advantageous embodiment in FIG. 4 shown.
- the pressure relief valve 12 has a conically shaped piston 15, the spring-loaded by a spring 16 gas-tight rests on a mating contour 17. Now, the piston 15 by means of gas pressure (see Arrow on the left side of the throttle valve) is pressurized, so the pressure acting on the piston 15 gas pressure can compress the spring 16 against a stop 18. This opens a gap between the piston 15 and the mating contour 17, whereby gas can pass through the pressure relief valve to the right.
- the gas pressure-dependent flow rate of the premix gas by the pressure relief valve 12 is set individually.
- the entire device is structurally simple and inexpensive to produce.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Feeding And Controlling Fuel (AREA)
Description
Die Erfindung bezieht sich auf eine Vorrichtung mit einem Vormischbrenner, einer Brennstoffversorgung und einer Steuer- oder Regeleinheit zum Betrieb einer Gasturbine, wobei der Vormischbrenner wenigstens eine, einen sich axial erstreckenden Vormischraum wenigstens teilweise begrenzende Brennerschale aufweist, mit einer in den Vormischraum über die Brennerschale gerichteten Premixgaszuführung, wobei das Premixgas mit Verbrennungszuluft vermischt und stromab, außerhalb des Vormischbrenners entzündet wird.The invention relates to a device with a premix burner, a fuel supply and a control unit for operating a gas turbine, wherein the premix burner has at least one burner shell at least partially delimiting an axially extending premixing chamber, with one directed into the premixing chamber via the burner cup Premix gas supply, wherein the premix gas is mixed with combustion air and ignited downstream, outside the premix burner.
Vormischbrenner der vorstehend genannten Gattung sind zum Betrieb von Gasturbinenanlagen hinlänglich bekannt und weisen unterschiedliche Vormischbrennergeometrien auf. So ist in der
Eine andere Vormischbrennergeometrie ist in der
Nun ist es möglich, durch geeignete Wahl der Anordnung, Größe, Anzahl der Austrittsöffnungen sowie deren gegenseitiger Abstand hinsichtlich der Qualität der Verbrennung Optimierungen vorzunehmen. So können insbesondere die Emissionswerte, das Auslöschverhalten der sich in der Brennkammer ausbildenden Flamme, das Flammenrückströmverhalten sowie die Flammenstabilität durch geeignete Wahl der vorstehend genannten Parameter entscheidend beeinflusst werden.Now it is possible to make optimizations by suitable choice of the arrangement, size, number of outlet openings and their mutual distance with regard to the quality of the combustion. In particular, the emission values, the extinguishing behavior of the flame forming in the combustion chamber, the flame backflow behavior and the flame stability can be decisively influenced by a suitable choice of the abovementioned parameters.
Die vorstehend beschriebenen Optimierungsmöglichkeiten stoßen jedoch schnell auf Grenzen, sofern man Maßnahmen ergreifen möchte, um das Brennerverhalten nicht nur bei einer fest vorgegebenen Brennergeometrie sowie bei einem idealen Verbrennungszustand zu optimieren. So ist es nahezu unmöglich, mit einer konstruktiv vorgegebenen Anordnung von Austrittsöffnungen entlang bestimmter Bereiche der Brennerschalen das Verbrennungsverhalten bei unterschiedlichen Last- und Umgebungsbedingungen auf einem nahezu gleichbleibend optimalen Niveau zu halten. Es hat sich herausgestellt, dass sich eine optimierte Anordnung von Austrittsöffnungen für die Premixgaszuführung innerhalb des Vormischbrenners, der für den Einsatz eines bestimmten Maschinentyps optimal ausgelegt worden ist, beispielsweise für den Einsatz an einer Ringbrennkammer, nur schlecht oder überhaupt nicht für den Einsatz in einem anderen Maschinentyp, beispielsweise für den Einsatz in einer Silo-Brennkammer, verwenden lässt.However, the optimization possibilities described above quickly reach their limits if one wishes to take measures to optimize the burner behavior not only with a fixed burner geometry and with an ideal combustion state. Thus, it is almost impossible to keep the combustion behavior at a virtually constant optimum level with a structurally predetermined arrangement of outlet openings along certain areas of the burner shells, the combustion behavior under different load and ambient conditions. It has been found that an optimized arrangement of outlet ports for the premix gas supply within the premix burner, which has been optimally designed for the use of a particular type of machine, for example, for use in an annular combustion chamber, poor or not at all for use in another Machine type, for example, for use in a silo combustion chamber, use.
Auch treten im Laufe des Einsatzes eines Brenners schleichende Brennersystemveränderungen auf, die durch Ermüdungserscheinungen hervorgerufen werden und beispielsweise zu einer Erhöhung von Leckage-Luftströmungen führen. Durch die fest vorgegebene Anordnung der Premixgasdurchtrittsöffnungen, die selbst keinen oder nur vernachlässigbaren Alterungserscheinungen unterworfen sind, können die alterungsbedingten Veränderungen jeodch nicht kompensiert werden, wodurch eine Verschlechterung des Verbrennungsprozesses mit zunehmender Laufzeit des Brenners unausweichlich ist.Also occur during the use of a burner creeping burner system changes that are caused by fatigue and lead, for example, to an increase in leakage air currents. Due to the fixed predetermined arrangement of Premixgasdurchtrittsöffnungen, which are themselves subject to no or only negligible aging phenomena, the aging-related changes can not be compensated jeodch, whereby a deterioration of the combustion process with increasing duration of the burner is inevitable.
Bestehende Premixgaszuführsysteme werden in der Regel für den mittleren und hohen Lastbereich von Gasturbinen hinsichtlich niedriger Emissionswerte und gedämpftem Auftreten von Verbrennungsoszillationen optimiert. Um den Verbrennungsprozess zu starten sowie den mittleren Lastbereich der Gasturbine zu erreichen, werden üblicherweise Pilotierungsstufen eingesetzt. Üblicherweise wird mittig zur Vormischbrennerachse über eine Brennerlanze Pilotgas in das Innere des Vormischbrenners eingespeist, das sich mit Verbrennungszuluft mischt und zur Zündung gebracht wird. Erst nach Erreichen eines bestimmten Lastbereiches wird die Pilotgaszuführung ausgeschaltet und die Premixgaszufuhr in Betrieb genommen werden. In gleicher Weise erfolgt eine derartige Umschaltung beim Herunterfahren der Gasturbine, bei der die Premixgaszufuhr abgeschaltet und die Pilotgaszuführung eingeschaltet wird. Bei den Umschaltprozessen treten jedoch hohe Verbrennungsoszillationen innerhalb des Brennersystems auf, die mit starken Druckschwankungen verbunden sind, die wiederum eine unmittelbare und störende Auswirkung auf das Lastverhalten der Gasturbine nach sich ziehen, die in Folge dessen großen Lastschwingungen unterworfen wird.Existing premix gas supply systems are typically optimized for the medium and high load ranges of gas turbines in terms of low emissions and cushioned combustion oscillations. In order to start the combustion process and to reach the middle load range of the gas turbine, pilot stages are usually used. Usually, pilot gas is fed into the interior of the premix burner in the center of the premix burner axis via a burner lance, which mixture is mixed with combustion air and brought to ignition. Only after reaching a certain load range, the pilot gas supply is switched off and the Premixgaszufuhr be put into operation. In the same way, such switching occurs when the gas turbine is shut down, in which the premix gas supply is switched off and the pilot gas supply is switched on. In the switching processes, however, high combustion oscillations occur within the burner system, which are associated with strong pressure fluctuations, which in turn have an immediate and disturbing effect on the load behavior of the gas turbine, which is consequently subjected to large load oscillations.
Wird ein Gaszuführungssystem sowohl beim Hoch- als auch beim Herunterfahren der Gasturbine abgeschaltet, so ist es erforderlich, die abgeschalteten Gaszufuhrleitungen mit Inertgas zu reinigen, um Rückzündungen in die Zuführleitung hinein auszuschließen und deren Beschädigungen zu vermeiden. Die zur Reinigung der Gaszuleitung benötigte Menge an Inertgasen nimmt ein beträchtliches Ausmaß an und führt nicht zuletzt auch zu hohen Betriebskosten derartiger Brennersysteme.When a gas supply system is shut down both when the gas turbine is raised and lowered, it is necessary to purify the shut-off gas supply lines with inert gas in order to re-ignite the gas To exclude supply line into it and to avoid their damage. The amount of inert gases required for the purification of the gas supply takes on a considerable extent and not least also leads to high operating costs of such burner systems.
Schließlich ist es mit den derzeit bekannten Vormischbrennern nahezu unmöglich, den Vormischbrenner mit unterschiedlichen Brennstoffsorten, wie beispielsweise flüssigem oder gasförmigem Brennstoff, zu betreiben, zumal die in der Regel mittig in der Brennerachse angeordnete Brennerlanze zur Zuführung von Pilotgas, das wie vorstehend erwähnt, zum Hochfahren der Gasturbine sowie für den unteren Lastbereich erforderlich ist, in unmittelbarer räumlicher Nähe zur zentralen Flüssigbrennstoffdüse angeordnet ist. Ungewollte Zündwechselwirkungen zwischen beiden Brennstoffauslässen können nicht ausgeschlossen werden.Finally, with the presently known premix burners, it is almost impossible to operate the premix burner with different types of fuel, such as liquid or gaseous fuel, especially as the burner lance generally arranged centrally in the burner axis for supplying pilot gas, as mentioned above, for powering up the gas turbine and for the lower load range is required, is located in close proximity to the central liquid fuel nozzle. Unintended ignition interactions between the two fuel outlets can not be excluded.
Die beiden Schriften
Der Erfindung liegt die Aufgabe zugrunde, eine Vorrichtung mit einem Vormischbrenner, einer Brennstoffversorgung und einer Steuer- oder Regeleinheit gemäß dem Oberbegriff des Anspruchs 1 derart weiterzubilden, dass die vorstehend zum Stand der Technik angeführten Nachteile vermieden werden. Insbesondere gilt es, Maßnahmen am Vormischbrenner zu treffen, so dass eine optimierte Anpassung des Vormischbrennerverhaltens im gesamten Lastbereich der Gasturbine möglich wird. Dies soll insbesondere ohne großen technischen und konstruktiven Aufwand erfolgen und mit nur geringen Kosten realisierbar sein.The invention has the object of providing a device with a premix burner, a fuel supply and a control or regulating unit according to the preamble of
Die Lösung der der Erfindung zugrunde liegenden Aufgabe ist im Anspruch 1 angegeben. Den Erfindungsgedanken vorteilhaft weiterbildende Merkmale sind Gegenstand der abhängigen Ansprüche sowie der Beschreibung, insbesondere unter Bezugnahme auf die Figuren zu entnehmen.The solution of the problem underlying the invention is specified in
Die der Erfindung zugrunde liegende Idee ist die axiale gestufte Zuführung von Premixgas entlang der Flanken der Brennerschalen, indem die Brennerschalen in wenigstens zwei axial hintereinander angeordnete Bereiche unterteilt sind, die jeweils über getrennt voneinander geführte Premixgaszuführleitungen versorgt werden. Die voneinander getrennten Bereiche entlang der Brennerschalen sind in Durchströmungsrichtung des Vormischbrenners axial hintereinander angeordnet, wobei erfindungsgemäß erkannt worden ist, dass zum Anfahren der Gasturbine mehr als 60 % der gesamten Premixgaszuführung über den stromauf ersten Bereich erfolgen soll und dass für das weitere Hochfahren der Last der Gasturbine bis Volllast eine stufenweise oder kontinuierliche Umverteilung der Premixgaszuführung auf die stromab nach dem ersten Bereich angrenzenden Bereiche erfolgt.The idea underlying the invention is the axial stepped supply of premix gas along the flanks of the burner shells by the burner shells are divided into at least two axially successively arranged areas, which are each supplied via Premixgaszuführleitungen separated. The separate areas along the burner shells are arranged axially behind one another in the direction of flow of the premix burner, wherein it has been recognized according to the invention that more than 60% of the total premix gas supply is to be made via the upstream first region for starting up the gas turbine and that the load is required for the further startup Gas turbine to full load a gradual or continuous redistribution of Premixgaszuführung on the downstream of the first area adjacent areas takes place.
Durch die axiale Unterteilung der Premixgaszuführung entlang der Brennerschalen des Vormischbrenners und insbesondere die stufenweise Versorgung der einzelnen Bereiche mit Premixgas ist es möglich, vollständig auf die Zufuhr von Pilotgas zu verzichten, selbst im Falle des Anfahrens sowie in unteren Lastbereichen der Gasturbine.Due to the axial subdivision of the Premixgaszuführung along the burner bowls of the premix burner and in particular the stepwise supply of the individual areas with premix gas, it is possible to completely dispense with the supply of pilot gas, even in the case of starting and in lower load ranges of the gas turbine.
Der Verzicht auf eine Pilotgasstufe ist mit einer Reihe von Vorteilen verbunden, die sich nicht zuletzt durch den Wegfall der durch die Umschaltung von Pilotgas zu Premixgaszufuhr verbundenen Brennkammeroszillationen ergeben.
Mit der erfindungsgemäßen Betriebsweise eines Vormischbrenners ist es erstmals möglich, eine Gasturbine vom Anfahren bis zur Volllast ohne eine Pilotgasstufe zu betreiben. Das kontinuierliche bzw. stufenhafte Zuschalten einzelner Bereiche, über die Premixgas in das Innere des Vormischbrenners gelangt, erfolgt mit Hilfe in den einzelnen Premixgaszuführleitungen vorgesehenen Steuer- bzw. Regeleinheiten, die im einfachsten Fall als regelbare Drosselventile ausgebildet sind.The elimination of a pilot gas stage is associated with a number of advantages, resulting not least by the elimination of the connected by the switching of pilot gas to Premixgaszufuhr Brennkammeroszillationen.
With the mode of operation of a premix burner according to the invention, it is now possible to operate a gas turbine from startup to full load without a pilot gas stage. The continuous or incremental connection of individual areas, via which premix gas enters the interior of the premix burner, takes place with the aid of provided in the individual Premixgaszuführleitungen control or regulating units, which are formed in the simplest case as a controllable throttle valves.
Durch den vorteilhaften Verzicht auf eine Pilotgaszufuhr ist es insbesondere möglich, durch eine zentrale, in den Brennermund hineinragende Einspritzdüse Flüssigbrennstoff zu zerstäuben, der seinerseits in geeigneter Weise mit einem schlauchförmig ausgebildeten Verbrennungsluftstrom umgeben ist.Due to the advantageous omission of a pilot gas supply, it is particularly possible to atomize liquid fuel through a central, projecting into the burner mouth injection nozzle, which in turn is suitably surrounded by a tubular combustion air flow.
Eine erfindungsgemäß ausgebildete Ausführungsform zur gezielten Zuflussregelung von Premixgas für die in unterschiedliche Bereiche unterteilten Brennerschalen des Vormischbrenners wird in der nachstehenden Beschreibung unter Bezugnahme auf die Figuren dargelegt. Wesentlicher Gesichtspunkt der nachstehend im Einzelnen beschriebenen Vorrichtung ist die getrennte, dosierte Premixgaszuführung zu den einzelnen, axial hintereinander angeordneten Bereichen entlang der Brennerschalen, durch die das Premixgas in das Innere des Vormischbrenners eingedüst wird.An embodiment designed according to the invention for the targeted supply control of premix gas for the burner shells of the premix burner subdivided into different regions is set out in the following description with reference to the figures. An essential aspect of the device described in detail below is the separate, metered premix gas supply to the individual, axially successively arranged regions along the burner shells, through which the premix gas is injected into the interior of the premix burner.
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnung exemplarisch beschrieben. Es zeigen:
Figur 1- schematische Querschnittsdarstellung durch einen kegelförmig ausgebildeten Vormischbrenner,
Figur 2- Diagrammdarstellung zur Betriebsweise der in
dargestellten Ausführungsform,Figur 1 Figur 3- schematisierter Plan zum Verlauf von Zufuhrleitungen zur Versorgung des Vormischbrenners mit Premixgas,
- Figur 4
- Ausführungsbeispiel eines Regelventils.
- FIG. 1
- schematic cross-sectional view through a cone-shaped premix burner,
- FIG. 2
- Diagram representation of the mode of operation of in
FIG. 1 illustrated embodiment, - FIG. 3
- schematic plan for the course of supply lines for supplying the premix burner with premix gas,
- FIG. 4
- Embodiment of a control valve.
In
Optional kann im Zentrum des Vormischbrenners eine Flüssigbrennstoffzerstäubungsrichtung 7 vorgesehen sein, die einen Mischbetrieb bzw. ein Umschalten von gasförmigem Brennstoff zu Flüssigbrennstoff erlaubt. Die Zufuhr von Flüssigbrennstoff erfolgt mit Hilfe einer an sich bekannten Zerstäubungsdüse, die eine sich kegelförmig ausbreitende Zerstäubungswolke innerhalb des Vormischbrenners erzeugt. Zum Schutz gegenüber den Premixgasaustrittsöffnungen 3 sowie zu Zwecken der Formstabilisierung wird die sich ausbreitende Flüssigbrennstoffwolke von einem Schutzluftmantel umgeben.Optionally, a liquid fuel atomization direction 7 can be provided in the center of the premix burner, which allows mixing operation or switching from gaseous fuel to liquid fuel. The supply of liquid fuel takes place with the aid of a known atomizing nozzle, which generates a conically spreading atomizing cloud within the premix burner. For protection against the
Zum Anfahren der Gasturbine, das heißt zum Zünden des Vormischbrenners, wird nicht, wie bei dem Stand der Technik üblich, eine Pilotierung vorgenommen, sondern in dem im Ausführungsbeispiel dargestellten zweistufigen Vormischbrenner wird jeder Bereich der Brennerschale mit einer Premixgaszufuhr versorgt, die stromauf innerhalb des Vormischbrenners angeordnet ist. Im Ausführungsbeispiel ist dies der Bereich Stufe 1, der zum Anfahren sowie zum Betreiben des Vormischbrenners im niedrigen Lastbereich mit mehr als 60 % der gesamten Premixgaszuführung betrieben wird.To start the gas turbine, that is to ignite the premix burner, a pilot is not, as is common in the prior art, made, but in the illustrated in the embodiment two-stage premix burner each area of the burner shell is supplied with a Premixgaszufuhr upstream in the premix burner is arranged. In the exemplary embodiment, this is the
Aus
Eine weitere Möglichkeit der kontrollierten Premixgaszuführung auf die getrennten Bereiche des Vormischbrenners ist aus der schematischen Darstellung gemäß
Das in
Ein derartiges Überdruckventil ist als vorteilhafte Ausführungsform in
Mit der erfindungsgemäßen Vorrichtung mit einem Vormischbrenner, einer Brennstoffversorgung und einer Steuer- oder Regeleinheit ist eine Reihe von Vorteilen verbunden: Durch die abgestufte Premixgaszuführung in den Vormischbrenner kann dieser in signifikant größeren Bereichsgrenzen eingesetzt werden als nur einstufig ausgelegte Vormischbrenner.With the device according to the invention with a premix burner, a fuel supply and a control or regulation unit, a number of advantages associated: By the graduated Premixgaszuführung in the premix burner this can be used in significantly larger range limits than just single-stage premix burner.
Mit Hilfe der in
Durch die Verwendung einer als Überdruckventil 12 ausgebildeten Regeleinheit ist zum Betreiben des Vormischbrenners lediglich eine einzige Regeleinheit erforderlich.By using a control unit designed as a
Die Nachrüstung an bereits bestehende Vormischbrennersysteme ist einfach durchführbar, zumal die Verwendung von zwei und mehr getrennten Premixgaszuleitungssystemen nicht erforderlich ist.The retrofitting to existing premix burner systems is easy to carry out, especially since the use of two or more separate Premixgaszuleitungssystemen is not required.
Durch die gezielte Zufuhr eines Minimumanteils von Premixgas in den zweiten Bereich des Vormischbrenners über die Bypassleitung ist es nicht erforderlich, diese Zufuhrleitung mit Erdgas zu reinigen. Versuche zeigten, dass das erfindungsgemäße System nur geringe Pulsationen im Anfahrverhalten hervorruft. Mit der individuellen Premixgaszuteilung auf die unterschiedlichen Bereiche des Vormischbrenners ist es möglich, auch bei auftretenden Alterungserscheinungen entsprechende Optimierungen vorzunehmen.
Aufgrund des möglichen Verzichtes einer Pilotgaszuführung können jegliche Pulsationen, die beim Umschalten zwischen Pilotgas- zu Premixgaszufuhr auftreten, vermieden werden.The targeted supply of a minimum proportion of premix gas in the second area of the premix burner via the bypass line, it is not necessary to clean this supply line with natural gas. Tests have shown that the system according to the invention only causes low pulsations in the starting behavior. With the individual Premixgaszuteilung on the different areas of the premix burner, it is possible to make appropriate optimizations even when occurring aging phenomena.
Due to the possible omission of a pilot gas supply, any pulsations that occur when switching between pilot gas to Premixgaszufuhr can be avoided.
Die gesamte Vorrichtung ist konstruktiv einfach und kostengünstig herstellbar.The entire device is structurally simple and inexpensive to produce.
- 1,21.2
- Brennerschalenburner shells
- 33
- PremixgasaustrittsöffnungenPremixgasaustrittsöffnungen
- 4,54.5
- PremixgaszuführleitungenPremixgaszuführleitungen
- 66
- Premixgaspremix gas
- 77
- FlüssigbrennstoffzerstäubungseinrichtungFlüssigbrennstoffzerstäubungseinrichtung
- 88th
- Zufuhrleitungsupply line
- 99
- HauptregeleinheitMain control unit
- 1010
- Kreuzungspunktintersection
- 1111
- Abzweigungsleitungbranch line
- 1212
- ÜberdruckventilPressure relief valve
- 1313
- Bypassleitungbypass line
- 1414
- Drosselelementthrottle element
- 1515
- Kolbenpiston
- 1616
- Federfeather
- 1717
- Gegenkonturmating contour
- 1818
- Anschlagattack
- S1, S2S1, S2
-
Bereiche 1, 2 für den gestuften Premixgasaustritt
1, 2 for the staged PremixgasaustrittAreas - AA
- BrennerachseBrenner
Claims (3)
- Device with a premix burner, a fuel supply and a control or regulator unit for operating a gas turbine, wherein the premix burner has at least one burner shell (1, 2) which at least partially delimits an axially extending premix chamber, and a premix gas supply directed into the premix chamber via the burner shell (1, 2), wherein the premix gas (6) is mixed with combustion supply air inside the premix burner and is ignited downstream outside the premix burner, wherein at least two physically separated regions (S1, S2) are provided axially along the burner shell (1, 2), via which regions premix gas (6) can be fed into the premix chamber and which are connected to separate premix gas supply lines (4, 5), wherein a first region (S1) is provided in the burner shell (1, 2) and arranged upstream in the premix burner, and at least one second region (S2) is arranged downstream of the first region (S1) in the premix burner, and a regulator or control unit is provided which is connected to the premix gas supply lines (4, 5) and divides the premix gas supply to the individual regions depending on the load range of the gas turbine,
characterised in that
the premix gas supply line (5) of the first region (S1) is provided with a choke valve (9), that an intersection point (10) is provided between the choke valve (9) and the first region (S1), from which point a branch line (11) leads to the second region (S2), and that the control or regulator unit is provided between the intersection point (10) and the second region (S2). - Device as claimed in claim 1, characterised in that the control or regulator unit is an overpressure valve (12) subjected to spring force.
- Device according to claim 1 or 2, characterised in that when the first region (S1) is supplied with premix gas (6), a bypass line (13) is provided between the intersection point (10) and the second region (S2) and ensures a minimum supply of premix gas (6) to the second region (S2) insofar as the first region (S1) is supplied with premix gas.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10049205A DE10049205A1 (en) | 2000-10-05 | 2000-10-05 | Process for supplying fuel to a premix burner for operating a gas turbine comprises introducing premix gas separately via two axially divided regions along the burner shell |
EP01970078A EP1334309B1 (en) | 2000-10-05 | 2001-10-03 | Method for supplying fuel to a premix burner |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01970078A Division EP1334309B1 (en) | 2000-10-05 | 2001-10-03 | Method for supplying fuel to a premix burner |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1855054A2 EP1855054A2 (en) | 2007-11-14 |
EP1855054A3 EP1855054A3 (en) | 2008-04-09 |
EP1855054B1 true EP1855054B1 (en) | 2016-08-17 |
Family
ID=7658698
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07113855.6A Expired - Lifetime EP1855054B1 (en) | 2000-10-05 | 2001-10-03 | Method for supplying fuel to a premix burner |
EP01970078A Expired - Lifetime EP1334309B1 (en) | 2000-10-05 | 2001-10-03 | Method for supplying fuel to a premix burner |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01970078A Expired - Lifetime EP1334309B1 (en) | 2000-10-05 | 2001-10-03 | Method for supplying fuel to a premix burner |
Country Status (7)
Country | Link |
---|---|
US (1) | US7003960B2 (en) |
EP (2) | EP1855054B1 (en) |
JP (1) | JP4143401B2 (en) |
CN (1) | CN1236227C (en) |
AU (1) | AU2001290191A1 (en) |
DE (2) | DE10049205A1 (en) |
WO (1) | WO2002029318A1 (en) |
Families Citing this family (15)
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DE10049203A1 (en) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Process for introducing fuel into a premix burner |
DE10051221A1 (en) * | 2000-10-16 | 2002-07-11 | Alstom Switzerland Ltd | Burner with staged fuel injection |
EP1510755B1 (en) * | 2003-09-01 | 2016-09-28 | General Electric Technology GmbH | Burner with lance and staged fuel supply. |
DE102004002631A1 (en) * | 2004-01-19 | 2005-08-11 | Alstom Technology Ltd | A method of operating a gas turbine combustor |
WO2005078348A1 (en) * | 2004-02-12 | 2005-08-25 | Alstom Technology Ltd | Premixing burner arrangement for operating a burner chamber and method for operating a burner chamber |
DE502006007811D1 (en) | 2005-06-17 | 2010-10-21 | Alstom Technology Ltd | Burner for premix-type combustion |
CN101297156B (en) * | 2005-09-05 | 2010-10-20 | 西门子公司 | Burner arrangement for a combustion chamber, associated combustion chamber and method for combusting fuel |
DE102006015529A1 (en) * | 2006-03-31 | 2007-10-04 | Alstom Technology Ltd. | Burner system with staged fuel injection |
US8147121B2 (en) * | 2008-07-09 | 2012-04-03 | General Electric Company | Pre-mixing apparatus for a turbine engine |
ES2576651T3 (en) | 2009-01-15 | 2016-07-08 | Alstom Technology Ltd | Burner of a gas turbine |
EP2348256A1 (en) * | 2010-01-26 | 2011-07-27 | Alstom Technology Ltd | Method for operating a gas turbine and gas turbine |
CN101846319B (en) * | 2010-05-26 | 2012-02-08 | 清华大学 | Weak cyclone stagnation gas burner |
CN109340752B (en) * | 2018-10-09 | 2019-09-03 | 新中天环保股份有限公司 | A kind of kiln hood multifunctional burner |
KR20220160546A (en) * | 2020-03-31 | 2022-12-06 | 미츠비시 파워 가부시키가이샤 | Gas Turbine Combustor and Gas Turbine |
US11774093B2 (en) | 2020-04-08 | 2023-10-03 | General Electric Company | Burner cooling structures |
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DE10049203A1 (en) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Process for introducing fuel into a premix burner |
DE10056124A1 (en) * | 2000-11-13 | 2002-05-23 | Alstom Switzerland Ltd | Burner system with staged fuel injection and method of operation |
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-
2000
- 2000-10-05 DE DE10049205A patent/DE10049205A1/en not_active Withdrawn
-
2001
- 2001-10-03 EP EP07113855.6A patent/EP1855054B1/en not_active Expired - Lifetime
- 2001-10-03 CN CN01816966.XA patent/CN1236227C/en not_active Expired - Fee Related
- 2001-10-03 US US10/381,784 patent/US7003960B2/en not_active Expired - Lifetime
- 2001-10-03 AU AU2001290191A patent/AU2001290191A1/en not_active Abandoned
- 2001-10-03 DE DE50113065T patent/DE50113065D1/en not_active Expired - Lifetime
- 2001-10-03 JP JP2002532858A patent/JP4143401B2/en not_active Expired - Fee Related
- 2001-10-03 WO PCT/IB2001/001819 patent/WO2002029318A1/en active IP Right Grant
- 2001-10-03 EP EP01970078A patent/EP1334309B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US7003960B2 (en) | 2006-02-28 |
EP1855054A3 (en) | 2008-04-09 |
EP1334309B1 (en) | 2007-09-26 |
JP4143401B2 (en) | 2008-09-03 |
AU2001290191A1 (en) | 2002-04-15 |
US20040029058A1 (en) | 2004-02-12 |
EP1334309A1 (en) | 2003-08-13 |
DE10049205A1 (en) | 2002-05-23 |
CN1236227C (en) | 2006-01-11 |
EP1855054A2 (en) | 2007-11-14 |
CN1468352A (en) | 2004-01-14 |
JP2004510918A (en) | 2004-04-08 |
WO2002029318A1 (en) | 2002-04-11 |
DE50113065D1 (en) | 2007-11-08 |
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