EP2436983A1 - Jet burner - Google Patents
Jet burner Download PDFInfo
- Publication number
- EP2436983A1 EP2436983A1 EP10186365A EP10186365A EP2436983A1 EP 2436983 A1 EP2436983 A1 EP 2436983A1 EP 10186365 A EP10186365 A EP 10186365A EP 10186365 A EP10186365 A EP 10186365A EP 2436983 A1 EP2436983 A1 EP 2436983A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- nozzle carrier
- jet
- pilot
- jet burner
- pilot nozzle
- 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.)
- Withdrawn
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2211/00—Thermal dilatation prevention or compensation
-
- 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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- 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
- F23R2900/00012—Details of sealing devices
-
- 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 invention relates to a jet burner with a jet pilot.
- a pilot nozzle holder for jet pilot nozzles arranged and fastened in the nozzle carrier for the premixing nozzles undergoes, in particular at the nozzle outlet, also different thermal loads than the nozzle carrier for the premixing nozzles, thereby causing thermal damage at the contact surfaces between premix nozzle carrier and pilot nozzle carrier Tensions can come.
- the object of the invention is to provide a jet burner with a jet pilot, which avoids these thermal stresses.
- the labyrinth seal comprises annular formations of the premixing nozzle carrier and the pilot nozzle carrier.
- the nozzle carriers are thus not only carriers of the labyrinth elements, but themselves form part of the sealing system.
- a head plate with openings for the pilot nozzles at the second end of the pilot nozzle carrier is arranged to suppress the hot gas entering the jet burner and for fixing pilot nozzles in the combustion chamber direction.
- an alignment plate is arranged on the flange of the pilot nozzle carrier, wherein the alignment plate has openings for fixing pilot nozzles in the radial direction relative to a longitudinal axis of the pilot nozzle carrier.
- the alignment plate serves as a floating bearing and allows thermal displacements of the central jet nozzles in the axial direction.
- premix nozzle carrier comprises jet nozzles arranged in a circle extending from its first end to the second end.
- pilot nozzle carrier comprises jet nozzles extending from its first end to the second end.
- At least three jet nozzles are arranged in the pilot nozzle carrier.
- the jet nozzles are arranged in the pilot nozzle carrier in a plane. It is also conceivable that a jet nozzle in the pilot nozzle carrier on the longitudinal axis of the pilot nozzle carrier and the other jet nozzles are arranged on a concentric ring. By a different arrangement of the pilot nozzles within the alignment plate results in a different number of recirculation zones.
- fuel pipes open into the jet nozzles.
- the fuel lances advantageously have a closed tip and upstream of the tip radial openings for the injection of fuel across to an oxidant stream.
- a gas turbine comprises a jet burner according to the invention.
- a premixing nozzle carrier having a first flange leaf is formed at its first end, at its second end, in such a way that it is used as part of the jet burner according to the invention.
- a pilot nozzle carrier is formed with a second flange at its first end, at its second end so that it is used as part of the jet burner according to the invention.
- a lifetime extension of the jet burner is achieved because thermal stresses and movement disabilities are avoided by thermal decoupling of the jet pilot. Permanent deformations caused by thermal stresses do not occur, which ensures reliable operation of the pilot. Due to a labyrinth seal the hot gas entering the burner is still not possible. Eliminating twisting by using a jet pilot results in less thermal acoustics, suppression of pressure pulsations, generation of small-scale flow structures, and dissipation of acoustically induced heat release fluctuations.
- the FIG. 1 shows schematically and by way of example a jet burner 1 with a jet pilot 2.
- the jet burner 1 comprises a nozzle carrier 3 for premixing nozzles (jet carrier) with a first 12 and a second end 13 and a pilot nozzle carrier 4 (pilot jet carrier).
- Premix nozzles 5 are arranged in a circular manner in the nozzle carrier 3.
- a head plate 11 closes the interior of the pilot nozzle carrier 4 from the combustion chamber.
- the openings 6 for the pilot nozzles 7 in the top plate 11 are in the embodiment of FIG. 1 arranged on a line.
- FIG. 2 shows the pilot nozzle carrier 4, which at a first end 8 has a flange 23, which will be referred to here as the second flange 23 and is closed at the second end 10 with the top plate 11 having openings 6 for the pilot nozzles 7.
- FIG. 3 shows the pilot nozzle carrier 4 from a different angle and without top plate 11th
- FIG. 4 shows a section through a jet burner 1 with a jet pilot 2 facing away from the combustion chamber and during operation colder, first end 8 of the pilot nozzle carrier or first end 12 of the Vormischdüsenvics 3.
- the pilot nozzle carrier 4 is in the central passage opening 25 of the premix nozzle carrier 4 via a first flange 22 on Vormischdüsenvic 3 and a second flange 23 on the pilot nozzle carrier 4, which form a threaded flange 9, fixed on one side and is at its second end 10, that is freely suspended, ie in the exit region.
- the second end 10 of the pilot nozzle carrier 4 and the second end 13 of the Vormischdüsenitatis 3 form a labyrinth seal 14. Radial and axial movements are possible within this labyrinth seal 14.
- FIG. 4 further shows an alignment plate 15 for the pilot nozzles 7 at the first end 8 of the pilot nozzle carrier 4.
- FIG. 5 illustrates the function of the labyrinth seal 14 with room for movements in the radial and axial directions (see arrows).
- FIG. 6 shows the alignment plate 15 with openings 24 for fixing pilot nozzles 7 in the radial direction relative to a longitudinal axis of the pilot nozzle carrier 4. It serves as a floating bearing and allows thermal shifts in the axial direction.
- FIG. 7 shows alignment plate 15, pilot nozzle carrier 4 and nozzle carrier 3 in the assembly.
- a first flange 22 on Vormischdüsenvic 3 and a second flange 23 on the pilot nozzle carrier 4 form a threaded flange 9.
- the alignment plate 15 rests on the second flange 23 on the pilot nozzle carrier 4.
- FIG. 8 demonstrates that the fuel supply of the jet pilot 2 takes place as well as usually in the premix burner, ie via fuel lances 16 in a so-called "cross flow" configuration.
- FIG. 9 shows this in detail, wherein a fuel lance 16 has a closed tip 17 and near the top radial openings 18, can be injected through the fuel 20 in a flowing past the fuel lance 16 air flow 19.
- FIGS. 10 and 11 show how a different number of recirculation zones 21 is created by a different arrangement of the pilot nozzles 7 within the top plate 11. By changing the nozzle diameter, the flow rate can be adjusted.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
Description
Die Erfindung betrifft einen Strahlbrenner mit einem Strahlpiloten.The invention relates to a jet burner with a jet pilot.
Auf vorgemischten Strahlflammen basierende Verbrennungssysteme 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 Stömungsstrukturen erzeugen, die akustisch induzierte Wärmefreisetzungsfluktuationen dissipieren und somit Druckpulsationen, die typisch für drallstabilisierte Flammen sind, unterdrücken.On premixed jet flame based combustion systems offer 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 suitable choice of the jet pulse, small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus suppress pressure pulsations typical of spin-stabilized flames.
Bisherige Strahlbrennersysteme wurden mittels eines Drallpiloten stabilisiert, welcher die oben beschriebenen Vorteile zumindest teilweise aufhebt. Um dies zu vermeiden, sollen anstelle der Drallpiloten Strahlpiloten zum Einsatz kommen.Previous jet burner systems have been stabilized by means of a twisting pilot, which at least partially overcomes the advantages described above. To avoid this, jet pilots should be used instead of the swirl pilots.
Ein im Düsenträger für die Vormischdüsen angeordneter und befestigter Pilotdüsenträger für Strahlpiloten erfährt jedoch aufgrund der unterschiedlichen Betriebszustände für Vormisch-und Pilotbetrieb insbesondere am Düsenaustritt auch andere thermische Belastungen als der Düsenträger für die Vormischdüsen, wodurch es an den Kontaktflächen zwischen VormischDüsenträger und Pilot-Düsenträger zu thermischen Spannungen kommen kann.However, due to the different operating states for premixing and pilot operation, a pilot nozzle holder for jet pilot nozzles arranged and fastened in the nozzle carrier for the premixing nozzles undergoes, in particular at the nozzle outlet, also different thermal loads than the nozzle carrier for the premixing nozzles, thereby causing thermal damage at the contact surfaces between premix nozzle carrier and pilot nozzle carrier Tensions can come.
Aufgabe der Erfindung ist es, einen Strahlbrenner mit einem Strahlpiloten anzugeben, der diese thermischen Spannungen vermeidet.The object of the invention is to provide a jet burner with a jet pilot, which avoids these thermal stresses.
Erfindungsgemäß wird diese Aufgabe gelöst durch die Vorrichtung gemäß Anspruch 1. Vorteilhafte Weiterbildungen der Erfindung sind in den abhängigen Ansprüchen definiert. Indem bei einem Strahlbrenner, umfassend einen im Wesentlichen zylinderförmigen Vormischdüsenträger mit einem ersten und einem zweiten Ende und einer zentralen Durchgangsöffnung mit einem Durchmesser und einen im Wesentlichen hohlzylinderförmigen Pilotdüsenträger mit einem ersten und einem zweiten Ende und einem Außendurchmesser, der kleiner ist, als der Durchmesser der zentralen Durchgangsöffnung des Vormischdüsenträgers, wobei ein erstes Flanschblatt am ersten Ende des Vormischdüsenträgers mit einem zweiten Flanschblatt am ersten Ende des Pilotdüsenträgers einen Flansch zum Fixieren des Pilotdüsenträgers im Vormischdüsenträger bildet und die zweiten Enden so ineinander greifen, dass eine Labyrinthdichtung gebildet wird, wird folgendes erreicht:
- Der gesamte Strahlpilot ist im Düsenträger (Jet Carrier) über einen geschraubten Flansch einseitig fixiert und im Austrittsbereich frei schwebend gelagert und somit thermisch entkoppelt. Radiale und axiale Bewegungen sind innerhalb dieser Labyrinthdichtung möglich. Dadurch werden thermische Spannungen und Bewegungsbehinderungen vermieden. Die Lagerung auf der kalten Seite vermeidet große Dehnungsunterschiede zwischen dem Düsenträger und der Strahlpilotenbaugruppe.
- The entire jet pilot is fixed on one side in the nozzle carrier (Jet Carrier) via a bolted flange and is suspended freely in the outlet area and thus thermally decoupled. Radial and axial movements are possible within this labyrinth seal. As a result, thermal stresses and movement disabilities are avoided. The cold side storage avoids large expansion differences between the nozzle carrier and the jet pilot assembly.
Es ist vorteilhaft, wenn die Labyrinthdichtung ringförmige Ausformungen des Vormischdüsenträgers und des Pilotdüsenträgers umfasst. Die Düsenträger sind somit nicht nur Träger der Labyrinthelemente, sondern bilden selbst einen Teil des Dichtungssystems.It is advantageous if the labyrinth seal comprises annular formations of the premixing nozzle carrier and the pilot nozzle carrier. The nozzle carriers are thus not only carriers of the labyrinth elements, but themselves form part of the sealing system.
Zweckmäßiger Weise ist zur Unterdrückung des Heißgaseintritts in den Strahlbrenner und zur Fixierung von Pilotdüsen in Brennkammerrichtung eine Kopfplatte mit Öffnungen für die Pilotdüsen am zweiten Ende des Pilotdüsenträgers angeordnet.Appropriately, a head plate with openings for the pilot nozzles at the second end of the pilot nozzle carrier is arranged to suppress the hot gas entering the jet burner and for fixing pilot nozzles in the combustion chamber direction.
Vorteilhafter Weise ist eine Ausrichtplatte auf dem Flansch des Pilotdüsenträgers angeordnet, wobei die Ausrichtplatte Öffnungen zur Fixierung von Pilotdüsen in radialer Richtung bezogen auf eine Längsachse des Pilotdüsenträgers aufweist. Die Ausrichtplatte dient als Loslager und lässt thermische Verschiebungen der zentralen Strahldüsen in axialer Richtung zu.Advantageously, an alignment plate is arranged on the flange of the pilot nozzle carrier, wherein the alignment plate has openings for fixing pilot nozzles in the radial direction relative to a longitudinal axis of the pilot nozzle carrier. The alignment plate serves as a floating bearing and allows thermal displacements of the central jet nozzles in the axial direction.
Es ist zweckmäßig, wenn der Vormischdüsenträger sich von seinem ersten zum zweiten Ende erstreckende, kreisförmig angeordnete Strahldüsen umfasst.It is expedient if the premix nozzle carrier comprises jet nozzles arranged in a circle extending from its first end to the second end.
Ebenso ist es zweckmäßig, wenn der Pilotdüsenträger sich von seinem ersten zum zweiten Ende erstreckende Strahldüsen umfasst.It is likewise expedient if the pilot nozzle carrier comprises jet nozzles extending from its first end to the second end.
Vorteilhafter Weise sind mindestens drei Strahldüsen im Pilotdüsenträger angeordnet. Beispielsweise sind die Strahldüsen im Pilotdüsenträger in einer Ebene angeordnet. Denkbar ist auch, dass eine Strahldüse im Pilotdüsenträger auf der Längsachse des Pilotdüsenträgers und die weiteren Strahldüsen auf einem konzentrischen Ring angeordnet sind. Durch eine unterschiedliche Anordnung der Pilotdüsen innerhalb der Ausrichtplatte entsteht eine unterschiedliche Anzahl von Rezirkulationszonen.Advantageously, at least three jet nozzles are arranged in the pilot nozzle carrier. For example, the jet nozzles are arranged in the pilot nozzle carrier in a plane. It is also conceivable that a jet nozzle in the pilot nozzle carrier on the longitudinal axis of the pilot nozzle carrier and the other jet nozzles are arranged on a concentric ring. By a different arrangement of the pilot nozzles within the alignment plate results in a different number of recirculation zones.
Vorteilhafter Weise münden Brennstoffrohre (Lanzen) in die Strahldüsen. Die Brennstoff-Lanzen weisen vorteilhafter Weise eine geschlossene Spitze und stromauf der Spitze radiale Öffnungen für die Eindüsung von Brennstoff quer zu einem Oxidationsmittelstrom auf. Durch diese Art der Eindüsung des Brennstoffs in den Oxidationsmittelstrom wird eine besonders gute Durchmischung der Ströme erzielt.Advantageously, fuel pipes (lances) open into the jet nozzles. The fuel lances advantageously have a closed tip and upstream of the tip radial openings for the injection of fuel across to an oxidant stream. By this type of injection of the fuel into the oxidant stream, a particularly good mixing of the streams is achieved.
Vorteilhafter Weise umfasst eine Gasturbine einen erfindungsgemäßen Strahlbrenner.Advantageously, a gas turbine comprises a jet burner according to the invention.
Es ist vorteilhaft, wenn ein Vormischdüsenträger mit einem ersten Flanschblatt an seinem ersten Ende, an seinem zweiten Ende so ausgebildet ist, dass er als Teil des erfindungsgemä-βen Strahlbrenners Verwendung findet.It is advantageous if a premixing nozzle carrier having a first flange leaf is formed at its first end, at its second end, in such a way that it is used as part of the jet burner according to the invention.
Weiterhin ist es vorteilhaft, wenn ein Pilotdüsenträger mit einem zweiten Flanschblatt an seinem ersten Ende, an seinem zweiten Ende so ausgebildet ist, dass er als Teil des erfindungsgemäßen Strahlbrenners Verwendung findet.Furthermore, it is advantageous if a pilot nozzle carrier is formed with a second flange at its first end, at its second end so that it is used as part of the jet burner according to the invention.
Durch die Erfindung wird eine Lebensdauerverlängerung des Strahlbrenners erzielt, weil thermische Spannungen und Bewegungsbehinderungen durch thermische Entkoppelung des Strahlpiloten vermieden werden. Durch thermische Spannungen hervorgerufene dauerhafte Verformungen treten nicht auf, was einen verlässlichen Betrieb des Piloten gewährleistet. Durch eine Labyrinthdichtung ist der Heißgaseintritt in den Brenner trotzdem nicht möglich. Der Verzicht auf Verdrallung durch Verwendung eines Strahlpiloten führt zu geringerer Thermoakustik, zu Unterdrückung von Druckpulsationen, zur Erzeugung kleinskaliger Stömungsstrukturen und zur Dissipation akustisch induzierter Wärmefreisetzungsfluktuationen.By the invention, a lifetime extension of the jet burner is achieved because thermal stresses and movement disabilities are avoided by thermal decoupling of the jet pilot. Permanent deformations caused by thermal stresses do not occur, which ensures reliable operation of the pilot. Due to a labyrinth seal the hot gas entering the burner is still not possible. Eliminating twisting by using a jet pilot results in less thermal acoustics, suppression of pressure pulsations, generation of small-scale flow structures, and dissipation of acoustically induced heat release fluctuations.
Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen schematisch und nicht maßstäblich:
Figur 1- einen Strahlbrenner mit Strahlpiloten,
Figur 2- einen Pilotdüsenträger mit Kopfplatte,
Figur 3- einen Pilotdüsenträger,
Figur 4- einen Schnitt durch einen Strahlbrenner mit Strahlpiloten,
Figur 5- eine Labyrinthdichtung,
Figur 6- eine Ausrichtplatte,
Figur 7- Düsenträger, Strahlpilot und Ausrichtplatte zusammengebaut,
Figur 8- einen weiteren Schnitt durch einen Strahlbrenner mit Strahlpiloten inklusive der Brennstoffrohre,
Figur 9- einen Schnitt durch eine Strahldüse mit Brennstoffrohr,
Figur 10- eine Variante der Pilotdüsenanordnung und
Figur 11- eine weitere Variante der Pilotdüsenanordnung.
- FIG. 1
- a jet burner with jet pilot,
- FIG. 2
- a pilot nozzle carrier with head plate,
- FIG. 3
- a pilot nozzle carrier,
- FIG. 4
- a section through a jet burner with jet pilot,
- FIG. 5
- a labyrinth seal,
- FIG. 6
- an alignment plate,
- FIG. 7
- Nozzle carrier, jet pilot and alignment plate assembled,
- FIG. 8
- another section through a jet burner with jet pilots including the fuel pipes,
- FIG. 9
- a section through a jet nozzle with fuel pipe,
- FIG. 10
- a variant of the pilot nozzle assembly and
- FIG. 11
- another variant of the pilot nozzle assembly.
Die
Die
Claims (14)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10186365A EP2436983A1 (en) | 2010-10-04 | 2010-10-04 | Jet burner |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10186365A EP2436983A1 (en) | 2010-10-04 | 2010-10-04 | Jet burner |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2436983A1 true EP2436983A1 (en) | 2012-04-04 |
Family
ID=43629699
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10186365A Withdrawn EP2436983A1 (en) | 2010-10-04 | 2010-10-04 | Jet burner |
Country Status (1)
Country | Link |
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EP (1) | EP2436983A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014139738A1 (en) * | 2013-03-13 | 2014-09-18 | Siemens Aktiengesellschaft | Jet burner with cooling duct in the base plate |
WO2016160010A1 (en) * | 2015-04-01 | 2016-10-06 | Siemens Energy, Inc. | Pre-mixing based fuel nozzle for use in a combustion turbine engine |
CN110566947A (en) * | 2019-09-16 | 2019-12-13 | 浙江力聚热水机有限公司 | Ultra-low nitrogen premixed gas burner and burning method thereof |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4100733A (en) * | 1976-10-04 | 1978-07-18 | United Technologies Corporation | Premix combustor |
US4408461A (en) * | 1979-11-23 | 1983-10-11 | Bbc Brown, Boveri & Company Limited | Combustion chamber of a gas turbine with pre-mixing and pre-evaporation elements |
US5103632A (en) * | 1990-01-29 | 1992-04-14 | Sundstrand Corporation | Seal for a stored energy combustor |
US5339635A (en) * | 1987-09-04 | 1994-08-23 | Hitachi, Ltd. | Gas turbine combustor of the completely premixed combustion type |
-
2010
- 2010-10-04 EP EP10186365A patent/EP2436983A1/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4100733A (en) * | 1976-10-04 | 1978-07-18 | United Technologies Corporation | Premix combustor |
US4408461A (en) * | 1979-11-23 | 1983-10-11 | Bbc Brown, Boveri & Company Limited | Combustion chamber of a gas turbine with pre-mixing and pre-evaporation elements |
US5339635A (en) * | 1987-09-04 | 1994-08-23 | Hitachi, Ltd. | Gas turbine combustor of the completely premixed combustion type |
US5103632A (en) * | 1990-01-29 | 1992-04-14 | Sundstrand Corporation | Seal for a stored energy combustor |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014139738A1 (en) * | 2013-03-13 | 2014-09-18 | Siemens Aktiengesellschaft | Jet burner with cooling duct in the base plate |
US10088163B2 (en) | 2013-03-13 | 2018-10-02 | Siemens Aktiengesellschaft | Jet burner with cooling duct in the base plate |
WO2016160010A1 (en) * | 2015-04-01 | 2016-10-06 | Siemens Energy, Inc. | Pre-mixing based fuel nozzle for use in a combustion turbine engine |
CN110566947A (en) * | 2019-09-16 | 2019-12-13 | 浙江力聚热水机有限公司 | Ultra-low nitrogen premixed gas burner and burning method thereof |
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