EP2462379B1 - Stabilising of the flame of a burner - Google Patents
Stabilising of the flame of a burner Download PDFInfo
- Publication number
- EP2462379B1 EP2462379B1 EP10740607.6A EP10740607A EP2462379B1 EP 2462379 B1 EP2462379 B1 EP 2462379B1 EP 10740607 A EP10740607 A EP 10740607A EP 2462379 B1 EP2462379 B1 EP 2462379B1
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- EP
- European Patent Office
- Prior art keywords
- fluid
- jet
- reaction chamber
- burner
- burner according
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
- F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
- F23C9/06—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber for completing combustion
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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
- F23R3/34—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
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
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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
- F23C2202/00—Fluegas recirculation
- F23C2202/10—Premixing fluegas with fuel and combustion air
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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
- F23C2202/00—Fluegas recirculation
- F23C2202/20—Premixing fluegas with fuel
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation
Definitions
- the present invention relates to a burner for stabilizing the flame of a gas turbine, which comprises a reaction space and several opening into the reaction chamber jet nozzles, wherein the jet nozzles by means of a fluid jet fluid is injected into the reaction space, wherein the fluid is burned in the reaction space to hot gas.
- the invention also relates to a method for stabilizing the flame of a burner of a gas turbine.
- Beam flame-based combustion systems offer advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view.
- By a suitable choice of the beam pulse small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus suppress pressure pulsations which are typical for spin-stabilized flames.
- the jet flames are stabilized by mixing in hot recirculating gases.
- the required temperatures of the recirculation zone can not be guaranteed in gas turbines, especially in the lower part load range, by the known ring arrangement of the beams with a central recirculation zone.
- the stabilization of a jet flame therefore remains an incompletely solved task.
- a burner according to the prior art is in DE 19505614 disclosed.
- Another object of the present invention is to provide an advantageous burner of a gas turbine for stabilizing the flame of such a burner. Another object of the present invention is to provide an advantageous To provide methods for stabilizing the flame of such a burner.
- the torch-related object is achieved by a burner for stabilizing the flame of a burner of a gas turbine according to claim 1.
- the object related to the method is solved by specifying a method according to claim 14.
- the dependent claims contain further, advantageous embodiments of the invention.
- the burner according to the invention of a gas turbine comprises a reaction space and a plurality of jet nozzles opening into the reaction space.
- the jet nozzles With the jet nozzles, fluid is injected into the reaction space by means of a fluid jet. The fluid in the reaction space is then burned to hot gas.
- the invention has recognized that the jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction.
- an annular gap is present, which is arranged around the fluid jet. This sucks a portion of the hot gas from the reaction space, so that it flows against the fluid flow direction in the annular gap.
- the hot gas is mixed with the fluid jet. This ensures a defined mixing of hot gases in one or more jets of a jet burner, thus ensuring a reliable ignition and thus a reliable stabilization of the entire burner.
- the hot gas mixing is done already in the jet nozzle.
- the static pressure difference between the combustion chamber / reaction space and the fluid flowing at high velocity is used in the nozzle, which has a lowered static pressure due to the high flow rates.
- the annular gap is formed by means of an insert tube, wherein according to the invention the insert tube has a thickening at the upstream end. If compressor air is fed with or without fuel as fluid past the feed tube to the nozzle, deflection losses can thus be avoided.
- the thickening is diffused in the flow direction.
- an increase in the static pressure difference between the combustion chamber and the fluid flowing in the nozzle at high speed can be effected.
- the sucked gases can have a high temperature, which can damage the burner under certain circumstances.
- the insert tube is at least partially made of high quality materials with and without coating, e.g. designed as a ceramic version with and without coating.
- the insert tube has at least one opening in order to inject the hot gas into the fluid jet.
- the at least one opening is arranged upstream.
- the hot gas is sucked through the annular gap directly into the nozzle and is injected through the openings in the fluid jet.
- the openings are therefore mounted in the directly limiting the fluid jet wall.
- the size of the openings and the height of the annular gap are designed so that a good hot gas mixing in the air or the air / fuel mixture is ensured in the jet nozzle and that in the partial load range, the mixture temperature is brought to a value that ensures reliable ignition ,
- the openings can be designed as a bore or slots, which can also be made at an angle.
- the insert tube is preferably designed to be diffused in the flow direction in the flow direction. Thus, also can increase the static pressure difference between the combustion chamber and causing the fluid flowing in the nozzle at a high speed.
- a second annular channel for guiding combustion air and / or fuel is provided around the insert tube.
- means for increasing the heat transfer are provided in the second annular channel.
- these agents are dimples and / or cooling fins and / or wings.
- all other cooling concepts such as impingement cooling, convective cooling are conceivable in which the compressor air or the compressor / fuel mixture is added to the reaction space.
- the cooling air flowing through the second annular channel and / or fuel cools the insert tube thus fluid downstream.
- the jet nozzle has a nozzle outlet with a diameter D.
- the nozzle outlet is offset from the annular gap in the flow direction.
- the offset comprises a length of 0-3 x diameter of the nozzle outlet. This ensures optimum intake, especially in partial load operation.
- the fluid is compressor air which is premixed with fuel, partially premixed, or non-premixed.
- the object related to the method is achieved by specifying a method for stabilizing the flame of a burner of a gas turbine, which comprises a reaction space and a plurality of jet nozzles opening into the reaction space, wherein the jet nozzles are used to inject fluid into the reaction space by means of a fluid jet Reaction space, the fluid is burned, creating a hot gas.
- annular gap is present, wherein the annular gap is formed by means of an insert tube, which according to the invention at the upstream end has a thickening, wherein the hot gas is partially sucked through the annular gap and against the fluid flow direction flows into the annular gap and within the jet nozzle the fluid jet is mixed.
- the fluid preferably flows into the reaction space at high speed.
- a pressure difference is formed between the reaction space and the fluid jet flowing into the reaction space.
- the fluid is formed at partial load operation of the burner from a fuel / compressor air mixture, and at full load from compressor air, which has only slightly or no fuel content.
- These nozzles thus act in partial load operation as a pilot burner with pilot beams.
- pilot beams are made smaller than the other beams, so that less air passes through these nozzles.
- a stabilization is guaranteed at partial load operation.
- the burner is configured with a plurality of jet nozzles, of which, however, only one or a few nozzles according to the invention are. These then act as "pilot" at partial load as described above and are supplied with little or no fuel at full load. This avoids that increased NOx values occur during base load operation.
- FIG. 1 shows a section of a gas turbine with a shaft 14 arranged along a shaft axis and not shown, and a parallel to the shaft axis 14 aligned combustion chamber 16 in a longitudinal section.
- the combustion chamber 16 is rotationally symmetrical about a combustion chamber axis 18.
- the combustion chamber axis 18 is arranged in this particular embodiment parallel to the shaft axis 14, wherein it can also run at an angle to the shaft axis 14, in extreme cases perpendicular to this.
- An annular housing 10 of the combustion chamber 16 surrounds a reaction space 5, which is likewise designed rotationally symmetrical about the combustion chamber axis 18.
- FIG. 2 schematically shows a section through a jet burner perpendicular to a shaft axis 14 of the burner.
- the burner comprises a housing 10 which has a circular cross-section. Within the housing 10, a certain number of jet nozzles 3 is arranged substantially annular. Each jet nozzle 3 has a circular cross section.
- the burner may include a pilot burner 25.
- FIG. 3 schematically shows a section through another jet burner, wherein the section is perpendicular to the central axis of the further burner.
- the burner also has a housing 10 which has a circular cross-section and in which a number of inner and outer jet nozzles 3,30 is arranged.
- the jet nozzles 3, 30 each have a circular cross-section, the outer jet nozzles 3 having an equal or larger cross-sectional area than the inner jet nozzles 30.
- the outer jet nozzles 3 are arranged essentially annularly inside the housing 10 and form an outer ring.
- the inner jet nozzles 30 are also arranged annularly within the housing 10.
- the inner jet nozzles 30 form an inner ring that is concentric with the outer jet nozzle ring.
- FIGS. 2 and 3 merely show examples of the arrangement of jet nozzles 3, 30 within a jet burner. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 3,30 possible.
- the jet flame-based combustion system offers advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view.
- By a suitable choice of the beam pulse small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus pressure pulsations, which are typical of spin-stabilizing flames, suppress.
- the jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction. This is achieved by means of the invention now.
- Fig. 4 shows a jet nozzle 6.
- the burner comprises a reaction chamber 5 and several opening into the reaction chamber 5 jet nozzles 6.
- the jet nozzle 2 fluid is injected into the reaction chamber 5 with a fluid jet.
- the fluid is burned to hot gas 4.
- the fluid may be a fuel / air mixture, or even be formed from compressor air.
- annular gap is now available. This is formed from an insert tube 12.
- the annular gap 8 is thus arranged around the fluid jet 2.
- Hot gas 4 is now sucked into the nozzle 6 through this annular gap 8.
- the particular static pressure difference between the combustion chamber 16 and the reaction chamber 5 and the fluid flowing at high speed fluid is used, which has a lowered static pressure due to the high flow rates.
- the annular gap 8 now hot gas 4 flows against the flow direction of the fluid jet 2 in the nozzle 6 in the nozzle 6 back. There, the hot gas 4 is mixed with the fluid jet 2.
- the hot gas admixture is thus according to the invention within the nozzle 6. This corresponds to a defined mixing of hot gas in the nozzle 6, whereby a reliable ignition and thus a reliable stabilization of the entire burner is ensured.
- the stabilization is particularly advantageous at partial load operation.
- only one or a few nozzles 6 of a jet burner can be configured with this device for the suction of hot gas 4. These can act as pilot burners at partial load operation.
- the fluid may be a fuel / air mixture.
- these "pilot beams" are made smaller than the other beams, so that less compressor air passes through these nozzles 6.
- the fluid can then consist essentially of compressor air. Thus, increased NOx levels can be avoided at base load.
- the hot gas is sucked in through the annular gap 8. This is formed by an insert tube 12. Upstream in the insert tube 12, one or more openings 11 are formed, by means of which the hot gas 4 can be added to the fluid jet 2.
- the openings 11 are in the insert tube 12 on the beam side, that is arranged in the beam limiting wall.
- the openings 11 can be designed as bores.
- the size of the openings 11 and the radial height H of the annular gap 8 are designed so that a good hot gas mixing is ensured in the fluid jet 2 in the jet nozzle 6.
- the nozzle 6 also has a nozzle outlet 22 with a diameter D.
- the nozzle outlet 22 can be arranged opposite the annular gap 8 offset in the flow direction.
- the offset 24 has a length L of 0mm-3x D (mm), where D is the diameter of the nozzle outlet 22.
- the mixture temperature is brought to a value that ensures reliable ignition and thus a reliable stabilization of the entire burner in all driving ranges.
- the fluid jet 2 may consist of an air / fuel mixture of different mixing quality.
- the jet flame itself can be premixed, partially premixed or not premixed.
- Fig. 5 shows a further second embodiment of a nozzle 6a.
- a second annular channel 20 is present, which is arranged around the annular gap 8 around.
- This annular channel 20 can essentially be designed to guide the compressor air or the air / fuel mixture to the nozzle inlet 28.
- the combustion air or the fuel / air mixture can serve for cooling particularly the radially outer wall of the insert tube 12. This is advantageous because the aspirated gases have a high temperature which otherwise could potentially damage the burner.
- the annular channel 20 may also be designed with heat transfer increasing measures.
- the hot gas-carrying passages so in particular the insert tube 12 made of high-quality materials, e.g. be made of ceramic or Keramikent ambiencen materials, the materials may still be coated.
- Fig. 6 shows an embodiment of a nozzle 6b according to the invention. It shows a nozzle, which in particular increases the static pressure difference between the combustion chamber 16 or the reaction space 5 and the fluid jet flow 2 at the level of the mixing point.
- Fig. 6 shows an insert tube 12a, which has a thickening 15 at the upstream end.
- the thickening 15 is executed rounded.
- the thickening 15 may be formed diffusely 16 in the flow direction. This results in a particularly efficient pressure difference increase.
- the openings 11 can also be designed as slots, which are optionally provided obliquely to.
- Fig. 7 has a nozzle 6c, in which the insert tube 12b is formed in the flow direction diffused 21 fluid flow side. Again, there is a particularly efficient pressure difference increase.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Gas Burners (AREA)
Description
Die vorliegende Erfindung betrifft einen Brenner zur Stabilisierung der Flamme einer Gasturbine, welcher einen Reaktionsraum und mehrere in den Reaktionsraum mündende Strahldüsen umfasst, wobei mit den Strahldüsen mittels eines Fluidstrahls Fluid in den Reaktionsraum eindüsbar ist , wobei das Fluid im Reaktionsraum zu Heißgas verbrannt wird. Die Erfindung betrifft auch ein Verfahren zur Stabilisierung der Flamme eines Brenners einer Gasturbine.The present invention relates to a burner for stabilizing the flame of a gas turbine, which comprises a reaction space and several opening into the reaction chamber jet nozzles, wherein the jet nozzles by means of a fluid jet fluid is injected into the reaction space, wherein the fluid is burned in the reaction space to hot gas. The invention also relates to a method for stabilizing the flame of a burner of a gas turbine.
Auf Strahlflammen basierende Verbrennungssysteme bieten gegenüber drallstabilisierten Systemen aufgrund der verteilten Wärmefreisetzungszonen und der fehlenden drallinduzierten Wirbel insbesondere aus thermoakustischer Sicht Vorteile. Durch geeignete Wahl des Strahlimpulses lassen sich kleinskalige Strömungsstrukturen erzeugen, die akustisch induzierte Wärmefreisetzungsfluktuationen dissipieren und somit Druckpulsationen, die für drallstabilisierte Flammen typisch sind, unterdrücken.Beam flame-based combustion systems offer advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view. By a suitable choice of the beam pulse, small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus suppress pressure pulsations which are typical for spin-stabilized flames.
Die Strahlflammen werden durch Einmischen heißer rezirkulierender Gase stabilisiert. Die hierfür nötigen Temperaturen der Rezirkulationszone können in Gasturbinen, insbesondere im unteren Teillastbereich, durch die bekannte Ringanordnung der Strahlen mit einer zentralen Rezirkulationszone nicht gewährleistet werden. Besonders im Teillastbereich muss daher dafür beachtet werden, dass durch zusätzliche Stabilisierungsmechanismen ein partielles bzw. komplettes Flammenverlöschen vermieden wird. Die Stabilisierung einer Strahlflamme bleibt daher eine nicht vollständig gelöste Aufgabe. Ein Brenner nach dem Stand der Technik ist in
Es ist daher die Aufgabe der vorliegenden Erfindung, einen vorteilhaften Brenner einer Gasturbine zur Stabilisierung der Flamme eines solchen Brenners zur Verfügung zu stellen. Eine weitere Aufgabe der vorliegenden Erfindung ist es, ein vorteilhaftes Verfahren zur Stabilisierung der Flamme eines solchen Brenners zur Verfügung zu stellen.It is therefore the object of the present invention to provide an advantageous burner of a gas turbine for stabilizing the flame of such a burner. Another object of the present invention is to provide an advantageous To provide methods for stabilizing the flame of such a burner.
Die auf den Brenner bezogene Aufgabe wird durch einen Brenner zur Stabilisierung der Flamme eines Brenners einer Gasturbine nach Anspruch 1 gelöst. Die auf das Verfahren bezogene Aufgabe wird durch die Angabe eines Verfahrens nach Anspruch 14 gelöst. Die abhängigen Ansprüche enthalten weitere, vorteilhafte Ausgestaltungen der Erfindung.The torch-related object is achieved by a burner for stabilizing the flame of a burner of a gas turbine according to claim 1. The object related to the method is solved by specifying a method according to
Dabei umfasst der erfindungsgemäße Brenner einer Gasturbine einen Reaktionsraum und mehrere in den Reaktionsraum mündende Strahldüsen. Mit den Strahldüsen wird mittels eines Fluidstrahls Fluid in den Reaktionsraum eingedüst. Das Fluid im Reaktionsraum wird anschließend zu Heißgas verbrannt.In this case, the burner according to the invention of a gas turbine comprises a reaction space and a plurality of jet nozzles opening into the reaction space. With the jet nozzles, fluid is injected into the reaction space by means of a fluid jet. The fluid in the reaction space is then burned to hot gas.
Die Erfindung hat erkannt, dass die auf Strahlflammen basierenden Verbrennungssysteme durch Einmischen heißer rezirkulierender Gase stabilisiert werden. Besonders im unteren Teillastbereich muss allerdings dafür Sorge getragen werden, dass durch zusätzliche Stabilisierungsmechanismen ein partielles bzw. komplettes Flammenverlöschen vermieden wird.The invention has recognized that the jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction.
Bei mindestens einer Strahldüse ist ein Ringspalt vorhanden, der um den Fluidstrahl angeordnet ist. Dieser saugt einen Teil des Heißgases aus dem Reaktionsraum an, so dass dieser entgegen der Fluidströmrichtung in den Ringspalt einströmt. Innerhalb der Strahldüse wird das Heißgas mit dem Fluidstrahl vermischt. Dies gewährleistet eine definierte Einmischung von Heißgasen in einen oder mehrere Strahlen eines Strahlbrenners, der somit eine verlässliche Zündung und damit eine verlässliche Stabilisierung des Gesamtbrenners gewährleistet. Die Heißgaseinmischung geschieht dabei bereits in der Strahldüse. Zur Ansaugung wird die statische Druckdifferenz zwischen Brennkammer/Reaktionsraum und dem mit hoher Geschwindigkeit strömenden Fluid in der Düse genutzt, welches durch die hohen Strömungsgeschwindigkeiten einen abgesenkten statischen Druck aufweist.In at least one jet nozzle an annular gap is present, which is arranged around the fluid jet. This sucks a portion of the hot gas from the reaction space, so that it flows against the fluid flow direction in the annular gap. Within the jet nozzle, the hot gas is mixed with the fluid jet. This ensures a defined mixing of hot gases in one or more jets of a jet burner, thus ensuring a reliable ignition and thus a reliable stabilization of the entire burner. The hot gas mixing is done already in the jet nozzle. For suction, the static pressure difference between the combustion chamber / reaction space and the fluid flowing at high velocity is used in the nozzle, which has a lowered static pressure due to the high flow rates.
Der Ringspalt ist mittels eines Einsatzrohres gebildet, wobei erfindungsgemäß das Einsatzrohr am stromaufwärtigen Ende eine Verdickung aufweist. Wird Verdichterluft mit öder ohne Brennstoff als Fluid am Einsatzrohr vorbei zu der Düse geführt, so können somit Umlenkverluste vermieden werden.The annular gap is formed by means of an insert tube, wherein according to the invention the insert tube has a thickening at the upstream end. If compressor air is fed with or without fuel as fluid past the feed tube to the nozzle, deflection losses can thus be avoided.
Vorteilhafterweise ist die Verdickung in Strömungsrichtung diffus ausgebildet. Somit kann eine Erhöhung der statischen Druckdifferenz zwischen der Brennkammer und den in der Düse mit hoher Geschwindigkeit strömenden Fluid bewirkt werden.Advantageously, the thickening is diffused in the flow direction. Thus, an increase in the static pressure difference between the combustion chamber and the fluid flowing in the nozzle at high speed can be effected.
Die eingesaugten Gase können eine hohe Temperatur haben, welche unter Umständen den Brenner schädigen können. Bevorzugt ist daher das Einsatzrohr zumindest teilweise aus hochwertigen Werkstoffen mit und ohne Beschichtung z.B. als keramische Ausführung mit und ohne Beschichtung ausgeführt.The sucked gases can have a high temperature, which can damage the burner under certain circumstances. Preferably, therefore, the insert tube is at least partially made of high quality materials with and without coating, e.g. designed as a ceramic version with and without coating.
Bevorzugt weist das Einsatzrohr mindestens eine Öffnung auf, um das Heißgas in den Fluidstrahl einzudüsen. In bevorzugter Ausgestaltung ist die mindestens eine Öffnung stromaufwärts angeordnet. Das Heißgas wird durch den Ringspalt direkt in die Düse eingesaugt und wird durch die Öffnungen in den Fluidstrahl eingedüst. Die Öffnungen sind daher in der direkt den Fluidstrahl begrenzenden Wand angebracht. Die Größe der Öffnungen als auch die Höhe des Ringspalts werden dabei so ausgelegt, dass eine gute Heißgaseinmischung in die Luft bzw. das Luft/Brennstoffluftgemisch in der Strahldüse gewährleistet ist und dass im Teillastbereich die Gemischtemperatur auf einen Wert gebracht wird, der eine sichere Zündung gewährleistet. Die Öffnungen können als Bohrung oder Schlitze ausgeführt sein, welche auch unter einem Winkel angestellt sein können.Preferably, the insert tube has at least one opening in order to inject the hot gas into the fluid jet. In a preferred embodiment, the at least one opening is arranged upstream. The hot gas is sucked through the annular gap directly into the nozzle and is injected through the openings in the fluid jet. The openings are therefore mounted in the directly limiting the fluid jet wall. The size of the openings and the height of the annular gap are designed so that a good hot gas mixing in the air or the air / fuel mixture is ensured in the jet nozzle and that in the partial load range, the mixture temperature is brought to a value that ensures reliable ignition , The openings can be designed as a bore or slots, which can also be made at an angle.
Bevorzugt ist das Einsatzrohr fluidstromseitig in Strömungsrichtung diffus ausgebildet. Somit kann ebenfalls eine Erhöhung der statischen Druckdifferenz zwischen der Brennkammer und den in der Düse mit hoher Geschwindigkeit strömenden Fluid bewirkt werden.The insert tube is preferably designed to be diffused in the flow direction in the flow direction. Thus, also can increase the static pressure difference between the combustion chamber and causing the fluid flowing in the nozzle at a high speed.
In vorteilhafter Ausgestaltung ist um das Einsatzrohr ein zweiter Ringkanal zur Führung von Verbrennungsluft und/oder Brennstoff vorgesehen. Vorteilhafterweise sind in dem zweiten Ringkanal Mittel zur Erhöhung des Wärmeübergangs vorgesehen. Dies bewirkt, dass das heißgasführende Einsatzrohr effizient gekühlt wird. Bevorzugt sind diese Mittel Dimpel und/oder Kühlrippen und/oder Wings. Allerdings sind auch alle anderen Kühlkonzepte wie Prallkühlung, Konvektivkühlung vorstellbar bei denen die Verdichterluft bzw. das Verdichter/Brennstoffgemisch in den Reaktionsraum gegeben wird. In bevorzugter Ausgestaltung kühlt die durch den zweiten Ringkanal strömende Kühlluft und/oder Brennstoff das Einsatzrohr damit fluidabstromseitig.In an advantageous embodiment, a second annular channel for guiding combustion air and / or fuel is provided around the insert tube. Advantageously, means for increasing the heat transfer are provided in the second annular channel. This causes the hot gas-carrying insert tube is cooled efficiently. Preferably, these agents are dimples and / or cooling fins and / or wings. However, all other cooling concepts such as impingement cooling, convective cooling are conceivable in which the compressor air or the compressor / fuel mixture is added to the reaction space. In a preferred embodiment, the cooling air flowing through the second annular channel and / or fuel cools the insert tube thus fluid downstream.
Vorteilhafterweise weist die Strahldüse einen Düsenauslass mit Durchmesser D auf. Bevorzugt ist der Düsenauslass gegenüber dem Ringspalt in Strömungsrichtung versetzt angeordnet. Vorteilhafterweise umfasst der Versatz eine Länge von 0-3 x Durchmesser des Düsenauslasses. Damit wird eine optimale Ansaugung vor allem im Teillastbetrieb gewährleistet.Advantageously, the jet nozzle has a nozzle outlet with a diameter D. Preferably, the nozzle outlet is offset from the annular gap in the flow direction. Advantageously, the offset comprises a length of 0-3 x diameter of the nozzle outlet. This ensures optimum intake, especially in partial load operation.
In bevorzugter Ausgestaltung ist das Fluid Verdichterluft, welche mit Brennstoff vorgemischt, teilvorgemischt oder nicht-vorgemischt ist.In a preferred embodiment, the fluid is compressor air which is premixed with fuel, partially premixed, or non-premixed.
Die auf das Verfahren bezogene Aufgabe wird durch die Angabe eines Verfahrens zur Stabilisierung der Flamme eines Brenners einer Gasturbine gelöst, welcher einen Reaktionsraum und mehrere in den Reaktionsraum mündende Strahldüsen umfasst, wobei mit den Strahldüsen mittels einem Fluidstrahl Fluid in den Reaktionsraum eingedüst wird, wobei im Reaktionsraum das Fluid verbrannt wird, wodurch ein Heißgas entsteht.The object related to the method is achieved by specifying a method for stabilizing the flame of a burner of a gas turbine, which comprises a reaction space and a plurality of jet nozzles opening into the reaction space, wherein the jet nozzles are used to inject fluid into the reaction space by means of a fluid jet Reaction space, the fluid is burned, creating a hot gas.
Bei mindestens einer Strahldüse ist ein Ringspalt vorhanden, wobei der Ringspalt mittels eines Einsatzrohres gebildet ist, welches erfindungsgemäß am stromaufwärtigen Ende eine Verdickung aufweist, wobei durch den Ringspalt das Heißgas teilweise angesaugt wird und entgegen der Fluidströmrichtung in den Ringspalt einströmt und innerhalb der Strahldüse dem Fluidstrahl beigemischt wird.In at least one jet nozzle, an annular gap is present, wherein the annular gap is formed by means of an insert tube, which according to the invention at the upstream end has a thickening, wherein the hot gas is partially sucked through the annular gap and against the fluid flow direction flows into the annular gap and within the jet nozzle the fluid jet is mixed.
Bevorzugt strömt das Fluid mit hoher Geschwindigkeit in den Reaktionsraum ein. Vorteilhafterweise wird zwischen dem Reaktionsraum und den in den Reaktionsraum strömenden Fluidstrahl eine Druckdifferenz gebildet.The fluid preferably flows into the reaction space at high speed. Advantageously, a pressure difference is formed between the reaction space and the fluid jet flowing into the reaction space.
Bevorzugt wird das Fluid bei Teillastbetrieb des Brenners aus einem Brennstoff/Verdichterluft Gemisch gebildet, und bei Volllast aus Verdichterluft, welche nur noch geringfügig oder gar keinen Brennstoffanteil aufweist. Diese Düsen wirken somit im Teillastbetrieb als Pilotbrenner mit Pilotstrahlen. Hierzu kann es zusätzlich vorteilhaft sein, dass diese "Pilotstrahlen" kleiner ausgeführt werden als die anderen Strahllen, damit weniger Luft durch diese Düsen tritt. Somit ist eine Stabilisierung bei Teillastbetrieb gewährleistet.Preferably, the fluid is formed at partial load operation of the burner from a fuel / compressor air mixture, and at full load from compressor air, which has only slightly or no fuel content. These nozzles thus act in partial load operation as a pilot burner with pilot beams. For this purpose, it may additionally be advantageous that these "pilot beams" are made smaller than the other beams, so that less air passes through these nozzles. Thus, a stabilization is guaranteed at partial load operation.
Es ist weiterhin vorteilhaft, das der Brenner mit mehreren Strahldüsen ausgestaltet ist, von denen jedoch nur eine bzw. einige wenige erfindungsgemäße Düsen sind. Diese wirken dann bei Teillast wie oben beschrieben als "pilot" und werden bei Volllastbetrieb mit wenig oder gar keinem Brennstoff beaufschlagt. Somit wird vermieden, dass bei Grundlastbetrieb erhöhte NOx Werten entstehen.It is also advantageous that the burner is configured with a plurality of jet nozzles, of which, however, only one or a few nozzles according to the invention are. These then act as "pilot" at partial load as described above and are supplied with little or no fuel at full load. This avoids that increased NOx values occur during base load operation.
Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung werden nachfolgend anhand von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren beschrieben.Further features, properties and advantages of the present invention will be described below by means of embodiments with reference to the accompanying figures.
Darin zeigen:
- FIG 1
- einen Ausschnitt aus einer Gasturbine mit einer Brennkammer in einem Längsschnitt entlang einer Wellenachse nach dem Stand der Technik,
- Fig. 2
- schematisch einen Schnitt durch einen Strahlbrenner quer zu dessen Längsrichtung,
- Fig. 3
- schematisch einen Schnitt durch einen weiteren Strahlbrenner quer zu dessen Längsrichtung,
- Fig. 4
- schematisch ein erstes Ausführungsbeispiel einer Düse 6, die keine erfindungsgemäße Verdickung zeigt,
- Fig. 5
- schematisch ein zweites Ausführungsbeispiel einer Düse 6a, die keine erfindungsgemäße Verdickung zeigt,
- Fig. 6
- schematisch ein drittes Ausführungsbeispiel einer erfindungsgemäßen Düse 6b,
- Fig. 7
- schematisch ein viertes Ausführungsbeispiel einer
Düse 6c, die keine erfindungsgemäße Verdickung zeigt.
- FIG. 1
- a section of a gas turbine with a combustion chamber in a longitudinal section along a shaft axis according to the prior art,
- Fig. 2
- FIG. 2 schematically a section through a jet burner transversely to its longitudinal direction, FIG.
- Fig. 3
- FIG. 2 schematically shows a section through a further jet burner transversely to its longitudinal direction, FIG.
- Fig. 4
- schematically a first embodiment of a
nozzle 6, which shows no thickening according to the invention, - Fig. 5
- schematically a second embodiment of a nozzle 6a, which shows no thickening according to the invention,
- Fig. 6
- schematically a third embodiment of a
nozzle 6b according to the invention, - Fig. 7
- schematically a fourth embodiment of a
nozzle 6c, which shows no thickening according to the invention.
Die
Die
Die
Die auf Strahlflammen basierenden Verbrennungssystem bieten gegenüber drallstabilisierten Systemen aufgrund der verteilten Wärmerfreisetzungszonen und der fehlenden drallinduzierten Wirbel insbesondere aus thermoakustischer Sicht Vorteile. Durch geeignete Wahl des Strahlimpulses lassen sich kleinskalige Strömungsstrukturen erzeugen, die akustisch induzierte Wärmefreisetzungsfluktuationen dissipieren und somit Druckpulsationen, die typisch für drallstabilisierende Flammen sind, unterdrücken. Die auf Strahlflammen basierenden Verbrennungssysteme werden durch Einmischen heißer rezirkulierender Gase stabilisiert. Besonders im unteren Teillastbereich muss allerdings dafür Sorge getragen werden, dass durch zusätzliche Stabilisierungsmechanismen ein partielles bzw. komplettes Flammenverlöschen vermieden wird. Dies wird mithilfe der Erfindung nun gelöst.The jet flame-based combustion system offers advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view. By a suitable choice of the beam pulse, small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus pressure pulsations, which are typical of spin-stabilizing flames, suppress. The jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction. This is achieved by means of the invention now.
Dabei kann das Fluid ein Brennstoff/Luft Gemisch sein, oder auch nur aus Verdichterluft gebildet werden.In this case, the fluid may be a fuel / air mixture, or even be formed from compressor air.
In der Strahldüse 6 ist nun ein Ringspalt vorhanden. Dieser wird aus einem Einsatzrohr 12 gebildet. Der Ringspalt 8 ist somit um den Fluidstrahl 2 angeordnet. Durch diesen Ringspalt 8 wird nun Heißgas 4 in die Düse 6 angesaugt. Zur Ansaugung des Heißgases 4 wird die insbesondere statische Druckdifferenz zwischen der Brennkammer 16 bzw. dem Reaktionsraum 5 und dem mit hoher Geschwindigkeit strömenden Fluid genutzt, welches durch die hohen Strömungsgeschwindigkeiten einen abgesenkten statischen Druck aufweist. Durch den Ringspalt 8 strömt nun Heißgas 4 entgegen der Strömungsrichtung des Fluidstrahls 2 in der Düse 6 in die Düse 6 zurück. Dort wird das Heißgas 4 dem Fluidstrahl 2 beigemischt.In the
Die Heißgasbeimischung erfolgt somit erfindungsgemäß innerhalb der Düse 6. Dies entspricht einer definierten Einmischung von Heißgas in der Düse 6, wodurch eine verlässliche Zündung und somit eine verlässliche Stabilisierung des Gesamtbrenners gewährleistet wird.The hot gas admixture is thus according to the invention within the
Die Stabilisierung ist insbesondere bei Teillastbetrieb vorteilhaft. Erfindungsgemäß können somit nur ein oder wenige Düsen 6 eines Strahlbrenners mit dieser Vorrichtung zur Ansaugung von Heißgas 4 ausgestaltet sein. Diese können bei Teillastbetrieb als Pilotbrenner wirken. Das Fluid kann dabei ein Brennstoff/Luft Gemisch sein. Hierzu kann es zusätzlich vorteilhaft sein, dass diese "Pilotstrahlen" kleiner ausgeführt werden als die anderen Strahlen, damit weniger Verdichterluft durch diese Düsen 6 tritt. Im Volllastbetrieb oder nahe der Volllast wird das Fluid nur noch mit wenig oder gar keinem Brennstoff beaufschlagt. Das Fluid kann dabei dann im Wesentlichen aus Verdichterluft bestehen. Somit können erhöhte NOx-Werte bei Grundlast vermieden werden.The stabilization is particularly advantageous at partial load operation. Thus, according to the invention, only one or a
Das Heißgas wird dabei über den Ringspalt 8 angesaugt. Dieser wird durch ein Einsatzrohr 12 gebildet. Stromaufwärts im Einsatzrohr 12 sind ein oder mehrere Öffnungen 11 gebildet, mittels denen das Heißgas 4 dem Fluidstrahl 2 beigemischt werden kann. Die Öffnungen 11 sind im Einsatzrohr 12 strahlseitig, das heißt in der den Strahl begrenzenden Wand angeordnet. Die Öffnungen 11 können dabei als Bohrungen ausgeführt sein.The hot gas is sucked in through the
Die Größe der Öffnungen 11 als auch die radiale Höhe H des Ringspalts 8 sind dabei so ausgeführt, dass eine gute Heißgaseinmischung in den Fluidstrahl 2 in der Strahldüse 6 gewährleistet ist.The size of the
Die Düse 6 weist zudem einen Düsenauslass 22 mit Durchmesser D auf. Der Düsenauslass 22 kann gegenüber dem Ringspalt 8 in Strömungsrichtung versetzt angeordert sein. Bevorzugt umfasst der Versatz 24 eine Länge L von 0mm-3x D (mm), wobei D der Durchmesser des Düsenauslasses 22 ist.The
Somit wird gerade im Teillastbereich die Gemischtemperatur auf einen Wert gebracht, die eine sichere Zündung und damit eine verlässliche Stabilisierung des Gesamtbrenners in allen Fahrbereichen gewährleistet.Thus, especially in the partial load range, the mixture temperature is brought to a value that ensures reliable ignition and thus a reliable stabilization of the entire burner in all driving ranges.
Der Fluidstrahl 2 kann dabei aus einen Luft/Brennstoffgemisch unterschiedlicher Mischungsgüte bestehen. Die Strahlflamme selber kann dabei vorgemischt, teil- vorgemischt oder nichtvorgemischt sein.The
Auch können die heißgasführenden Passagen, also insbesondere das Einsatzrohr 12 aus hochwertigen Werkstoffen z.B. aus keramischen oder Keramikenthaltigen Werkstoffen gefertigt sein, wobei die Werkstoffe noch beschichtet sein können.Also, the hot gas-carrying passages, so in particular the
Auch kann die Verdickung 15 in Strömungsrichtung diffus 16 ausgebildet sein. Somit ergibt sich eine besonders effiziente Druckdifferenzerhöhung. Die Öffnungen 11 können dabei auch als Schlitze, welche ggf. schräg an gestellt sind, ausgeführt sein.
Also, the thickening 15 may be formed diffusely 16 in the flow direction. This results in a particularly efficient pressure difference increase. The
Mit der hier vorgestellten Erfindung wird somit eine verlässliche Zündung und damit eine verlässliche Stabilisierung des Gesamtbrenners gewährleistet. Dabei werden angesaugte Heißgase 4 über einen Ringspalt 8 um den eigentlichen Strahl, das heißt, dem Fluidstrahl 2 angesaugt, und innerhalb der Düse 6 diesem Strahl 2 beigemischt. Als treibende Kraft wird dabei die statische Druckdifferenz zwischen Brennkammer und Strahlströmung eingesetzt. Insbesondere ist bei Teillastbetrieb eine solche Stabilisierung wichtig.With the invention presented here thus a reliable ignition and thus a reliable stabilization of the entire burner is guaranteed. In this case, sucked hot gases 4 are sucked in through an
Claims (17)
- Gas turbine burner which comprises a reaction chamber (5) and a plurality of jet nozzles (6) leading into the reaction chamber (5), wherein fluid can be injected through an outlet (22) by the jet nozzles (6) into the reaction chamber (5) by means of a fluid jet (2), the fluid being combusted in the reaction chamber (5) to produce hot gas (4), wherein
in at least one jet nozzle (6, 6a, 6b, 6c) an annular gap (8) is disposed around the fluid jet (2) such that some of the hot gas (4) can be drawn out of the reaction chamber (5) and flows into the annular gap (8) in the opposite direction to the fluid flow and is mixed with the fluid jet (2) inside the jet nozzle (6, 6a, 6b, 6c), and wherein the annular gap (8) is formed by means of a liner tube (12, 12a, 12b),
characterised in that
the liner tube (12a) has a thicker section (15) at the upstream end. - Burner according to claim 1,
characterised in that
the liner tube (12, 12a, 12b) has at least one orifice (11) for the purpose of injecting the hot gas (4) into the fluid jet (2). - Burner according to claim 2,
characterised in that
the at least one orifice (11) is disposed upstream of the outlet (22). - Burner according to one of claims 1-3,
characterised in that
the liner tube (12b) is embodied as diffuse (21) on the fluid flow side in the flow direction. - Burner according to one of claims 1-4,
characterised in that the thicker section (15) is embodied as diffuse (17) in the flow direction. - Burner according to one of claims 1-5, characterised in that
a second annular channel (20) is provided around the liner tube (12, 12a, 12b) for the purpose of ducting combustion air and/or fuel. - Burner according to claim 6,
characterised in that
means for increasing the transfer of heat are provided in the second annular channel (20). - Burner according to claim 7,
characterised in that
said means are dimples and/or cooling fins and/or wings. - Burner according to one of claims 6-8,
characterised in that
the means are disposed and embodied such that air and/or fuel thus flowing through the second annular channel (20) cools the liner tube (12,12a, 12b) on the fluid outflow side. - Burner according to one of the preceding claims,
characterised in that
the jet nozzle has a nozzle outlet (22) with diameter (D). - Burner according to claim 10,
characterised in that
the nozzle outlet (22) is arranged offset with respect to the annular gap (8) in the flow direction. - Burner according to claim 11,
characterised in that
the offset (24) has a length of 0 mm-3x diameter (D) mm. - Burner according to one of the preceding claims,
characterised in that
fluid can be injected through an outlet (22) by the jet nozzles (6) into the reaction chamber (5) by means of a fluid jet (2), wherein the fluid is compressor air which has been premixed, partially premixed or not premixed with fuel. - Method for stabilising the flame of a gas turbine burner which comprises a reaction chamber (5) and a plurality of jet nozzles (6) leading into the reaction chamber (5), wherein in the method fluid is injected by the jet nozzles (6) into the reaction chamber (5) by means of a fluid jet (2), the fluid being combusted in the reaction chamber (5), as a result of which a hot gas (4) is produced, wherein
in at least one jet nozzle (6) the hot gas (4) is partly sucked in through an annular gap (8) enclosed by the jet nozzle, wherein the annular gap (8) is formed by means of a liner tube (12, 12a, 12b), and the sucked-in hot gas (4) flows into the annular gap (8) in the opposite direction to the fluid flow and is admixed to the fluid jet (2) inside the jet nozzle (6),
characterised in that
the liner tube (12a) has a thicker section (15) at the upstream end. - Method according to claim 14,
characterised in that
the fluid flows at high velocity into the reaction chamber (5). - Method according to one of claims 14-15,
characterised in that
a pressure differential is formed between the reaction chamber (5) and the fluid jet (2) flowing into the reaction chamber (5). - Method according to one of claims 14-16,
characterised in that
in partial load operation of the burner the fluid is formed from a fuel/compressor air mixture, and at full load it is formed from compressor air having only a negligible fuel fraction or none at all.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10740607.6A EP2462379B1 (en) | 2009-08-03 | 2010-08-02 | Stabilising of the flame of a burner |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09167055A EP2295858A1 (en) | 2009-08-03 | 2009-08-03 | Stabilising of the flame of a burner |
EP10740607.6A EP2462379B1 (en) | 2009-08-03 | 2010-08-02 | Stabilising of the flame of a burner |
PCT/EP2010/061201 WO2011015549A1 (en) | 2009-08-03 | 2010-08-02 | Stabilizing the flame of a burner |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2462379A1 EP2462379A1 (en) | 2012-06-13 |
EP2462379B1 true EP2462379B1 (en) | 2016-03-30 |
Family
ID=41479366
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09167055A Withdrawn EP2295858A1 (en) | 2009-08-03 | 2009-08-03 | Stabilising of the flame of a burner |
EP10740607.6A Not-in-force EP2462379B1 (en) | 2009-08-03 | 2010-08-02 | Stabilising of the flame of a burner |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
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EP09167055A Withdrawn EP2295858A1 (en) | 2009-08-03 | 2009-08-03 | Stabilising of the flame of a burner |
Country Status (5)
Country | Link |
---|---|
US (1) | US9074762B2 (en) |
EP (2) | EP2295858A1 (en) |
CN (1) | CN102472485B (en) |
RU (1) | RU2533609C2 (en) |
WO (1) | WO2011015549A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
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US20140270731A1 (en) * | 2013-03-12 | 2014-09-18 | Applied Materials, Inc. | Thermal management apparatus for solid state light source arrays |
FR3018900B1 (en) * | 2014-03-19 | 2016-04-15 | Yahtec | BURNER DEVICE WITH PRE GAS MIX |
CN106415127B (en) | 2014-04-10 | 2020-09-15 | 索斐特公司 | Burner with a burner head |
CN106895399B (en) * | 2017-04-25 | 2024-08-09 | 武建斌 | Gasification combustion device for inside of alcohol-based fuel boiler |
CN109028043A (en) * | 2018-06-28 | 2018-12-18 | 广州市艾欣能能源科技有限责任公司 | A kind of energy-efficient boiler |
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US2918117A (en) * | 1956-10-04 | 1959-12-22 | Petro Chem Process Company Inc | Heavy fuel burner with combustion gas recirculating means |
US3174526A (en) * | 1960-08-23 | 1965-03-23 | Linde Robert Albert Von | Atomizing burner unit |
BE795261A (en) * | 1972-02-10 | 1973-05-29 | Bailey Frank W | BLUE FLAME RETENTION CANNON BURNERS AND HEAT EXCHANGER SYSTEMS |
US3927958A (en) * | 1974-10-29 | 1975-12-23 | Gen Motors Corp | Recirculating combustion apparatus |
US4004875A (en) * | 1975-01-23 | 1977-01-25 | John Zink Company | Low nox burner |
DE3033988C2 (en) * | 1980-09-10 | 1986-04-17 | Karl-Friedrich Dipl.-Ing. Dipl.-Wirtsch.-Ing. 4100 Duisburg Schmid | Gas burner with integrated burner head air cooling |
DE3902601A1 (en) * | 1989-01-28 | 1990-08-09 | Buderus Heiztechnik Gmbh | Forced-draught gas burner |
RU2008559C1 (en) * | 1991-04-15 | 1994-02-28 | Шестаков Николай Сергеевич | Method and device for burning gas |
US5240409A (en) * | 1992-04-10 | 1993-08-31 | Institute Of Gas Technology | Premixed fuel/air burners |
US5350293A (en) * | 1993-07-20 | 1994-09-27 | Institute Of Gas Technology | Method for two-stage combustion utilizing forced internal recirculation |
DE19505614A1 (en) * | 1995-02-18 | 1996-08-22 | Abb Management Ag | Operating method for pre-mixing burner |
RU2093750C1 (en) * | 1995-03-09 | 1997-10-20 | Самарский государственный технический университет | Method and device for gas combustion |
EP0911076A1 (en) * | 1997-10-23 | 1999-04-28 | Haldor Topsoe A/S | Reformer furnace with internal recirculation |
JP3924136B2 (en) | 2001-06-27 | 2007-06-06 | 三菱重工業株式会社 | Gas turbine combustor |
DE10217913B4 (en) * | 2002-04-23 | 2004-10-07 | WS Wärmeprozesstechnik GmbH | Gas turbine with combustion chamber for flameless oxidation |
SE0202836D0 (en) * | 2002-09-25 | 2002-09-25 | Linde Ag | Method and apparatus for heat treatment |
JP4422104B2 (en) | 2003-12-16 | 2010-02-24 | 株式会社日立製作所 | Gas turbine combustor |
EP1950494A1 (en) * | 2007-01-29 | 2008-07-30 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine |
EP2372245A1 (en) * | 2010-03-26 | 2011-10-05 | Siemens Aktiengesellschaft | Burner for stabilising the combustion of a gas turbine and method |
CN103562507B (en) * | 2012-05-25 | 2014-09-17 | 日野自动车株式会社 | Burner for exhaust gas purification device |
-
2009
- 2009-08-03 EP EP09167055A patent/EP2295858A1/en not_active Withdrawn
-
2010
- 2010-08-02 WO PCT/EP2010/061201 patent/WO2011015549A1/en active Application Filing
- 2010-08-02 RU RU2012108126/06A patent/RU2533609C2/en not_active IP Right Cessation
- 2010-08-02 US US13/388,304 patent/US9074762B2/en not_active Expired - Fee Related
- 2010-08-02 EP EP10740607.6A patent/EP2462379B1/en not_active Not-in-force
- 2010-08-02 CN CN201080034454.0A patent/CN102472485B/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
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US20120186265A1 (en) | 2012-07-26 |
WO2011015549A1 (en) | 2011-02-10 |
EP2462379A1 (en) | 2012-06-13 |
RU2012108126A (en) | 2013-09-10 |
CN102472485A (en) | 2012-05-23 |
US9074762B2 (en) | 2015-07-07 |
EP2295858A1 (en) | 2011-03-16 |
CN102472485B (en) | 2015-02-18 |
RU2533609C2 (en) | 2014-11-20 |
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