EP1062461B1 - Brennkammer und verfahren zum betrieb einer brennkammer - Google Patents
Brennkammer und verfahren zum betrieb einer brennkammer Download PDFInfo
- Publication number
- EP1062461B1 EP1062461B1 EP99913091A EP99913091A EP1062461B1 EP 1062461 B1 EP1062461 B1 EP 1062461B1 EP 99913091 A EP99913091 A EP 99913091A EP 99913091 A EP99913091 A EP 99913091A EP 1062461 B1 EP1062461 B1 EP 1062461B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion
- combustion chamber
- burner
- heat
- shield element
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
- F23D14/12—Radiant burners
- F23D14/16—Radiant burners using permeable blocks
-
- 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
- F23R3/002—Wall structures
-
- 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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic 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
- 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
- F23R3/346—Feeding into different combustion zones for staged combustion
Definitions
- the invention relates to a combustion chamber with a combustion chamber wall and with one of a variety of heat shield elements formed inner lining and a method for Operation of a combustion chamber.
- EP 0 576 697 B1 describes a combustion chamber of a gas turbine described in which, in addition to classic burner types catalytic burners are also used. As classic burner types, premix burners are used, with which the main combustion is carried out. Through the Combining these types of burners results in a simpler one Regulation with changing load conditions of the gas turbine.
- Such a two-stage combustion is also from the US 4,910,957 known in which the multi-stage combustion for Reduction of NOx emissions is used.
- a combustion gas turbine is known from DE-C-253 189 with an annular combustion chamber on its side walls each has a porous clay plate, which as so-called surface burner works.
- the Combustion chamber rear side through the porous clay plate led a fuel gas mixture.
- the fuel gas mixture is on the surface of the clay plate facing the combustion chamber ignited and burned to the surface. Through the radiated heat from the clay plate becomes a propellant for heated the drive of the combustion gas turbine.
- the object of the invention is to provide a combustion chamber which in a particularly simple design, a supply of fuel and of combustion air.
- Another object of the invention is the specification of a method for operating a combustion chamber, through which a stepped in a particularly simple manner Combustion is enabled.
- a combustion chamber Object achieved by a combustion chamber with a combustion chamber wall and with one of a variety of heat shield elements formed inner lining, at least one a heat shield element acting as a burner is a burner heat shield element is a fuel supply for supply of fuel and a combustion air supply for Combustion air supply are connected upstream.
- the burner heat shield element with numerous Cavities material, the fuel and the combustion air can be supplied so that combustion can be generated within this material.
- combustion is under construction enables in a particularly simple manner that a heat shield element, soft part of the fireproof inner lining the combustion chamber is used as a burner. a such burner heat shield element becomes fuel and combustion air for combustion in the heat shield element fed.
- Such a burner heat shield element represents a so-called Pore burner. Fuel and combustion air So burned in the cavities or pores, which is Material heats up. On the one hand, this leads to good stabilization the combustion. On the other hand, the pore structure works strongly dampening on combustion vibrations. This Both properties of a pore burner lead to the fact that there is almost no combustion in a pore burner Forms combustion vibration. The material continues to shine, which, as mentioned, strongly changes during combustion heats up a significant amount of heat. This leads to, that the flame temperature of the combustion within the material is comparatively low. This in turn has Consequence that less nitrogen oxides are formed. The advantage the lower flame temperature can also be used for this become more fuel and the burner heat shield element to supply less fuel to the burner in a first stage. This reduces the formation of such combustion vibrations, which is caused by the burner of the first stage can be.
- a pre-mixing space is preferred for the burner heat shield element upstream, into which the fuel and the combustion air can be initiated.
- Fuel and combustion air are first fed to the premixing room, where a fuel-air mixture is formed. This fuel-air mixture is then fed to the burner heat shield element. In order to the result is a homogeneous one which is favorable for the combustion Fuel-air mixture.
- the combustion chamber wall has an outside, along which preferably extends from a fuel line Fuel can be admitted into the premixing chamber.
- Fuel line could e.g. for an annular combustion chamber one in the circumferential direction of the annular combustion chamber around the combustion chamber wall circular ring line, from which e.g. also in simple Way for a variety of burner heat shield elements, which are arranged along this circumferential direction, fuel can be supplied.
- At least one burner is intended for a first stage of combustion, and being through the burner heat shield element downstream of the first stage a second stage of combustion can be generated.
- the burner heat shield element is simple realized a second stage of a two-stage combustion. Of course, further stages of combustion can also be provided his.
- the two-stage or multi-stage of Combustion becomes a reaction zone of combustion on one distributed larger volume. This results in the combustion chamber a lower tendency to form combustion vibrations. Such combustion vibrations can possibly substantial Cause damage in the combustion chamber.
- a two-stage or a multi-stage combustion a particularly good controllability for adaptation to different power outputs, i.e. Load conditions, e.g. for a gas turbine operated under different loads. Becomes a gas turbine through the exhaust gas from the combustion chamber is driven for combustion depending on the load the gas turbine-oriented fuel-air ratio required.
- At least two Burners have a wide range of parameters for control the combustion.
- e.g. - if necessary - The fuel supply to the burner heat shield element are omitted so that through the burner heat shield element only air flows into the combustion chamber.
- the air mass flow through the burner is the first Level can be reduced. This has in particular to Consequence that the burner can be made smaller. In order to e.g. the advantage that the burner in simpler Be removed from a surrounding housing can.
- the burner heat shield element extends along the Direction of expansion from a first end to a second End, the pre-mixing space preferably between the Combustion chamber wall and the burner heat shield element lies and an outlet opening being provided in the region of the second end that connects the premixing chamber with the combustion chamber.
- Cooling air can preferably be supplied to the burner heat shield element, the cooling air being used as combustion air is usable.
- the heat shield elements are often thereby cooled that cooling air from the outside of the combustion chamber wall e.g. through holes in the back of the heat shield elements to be led.
- this cooling air supply as a combustion air supply there is a special one simple supply of combustion air to the burner heat shield element.
- the material of the burner heat shield element is preferably the pore burner, a foamed ceramic, especially zirconium oxide or silicon carbide.
- a foamed ceramic especially zirconium oxide or silicon carbide.
- Such materials are z. B. producible in that in a foam-forming Carrier material the ceramic is introduced and after a foaming and curing of the carrier material is etched away, so that a porous ceramic remains.
- the combustion chamber is preferably an annular space forming annular combustion chamber, being along a circumferential direction of the annulus a plurality of heat shield elements is designed as a burner heat shield elements. Preferably is most of the along a circumferential direction arranged heat shield elements as burner heat shield elements educated. This results in a uniform Distribution of the second stage of combustion over the Circumference of the ring combustion chamber.
- the combustion chamber is preferred in a gas turbine, in particular used in a stationary gas turbine.
- the gas turbine has an output greater than 60 MW.
- According to the invention is directed to a method Problem solved by a method for operating a Combustion chamber with a combustion chamber wall and with one out of one A large number of inner lining elements formed, wherein at least one of the heat shield elements is fuel and supplied combustion air for combustion and the fuel and the combustion air within a porous structure of the heat shield element be burned.
- a first stage of combustion preferably runs first from, then a via the heat shield element second stage of combustion takes place.
- the method in a combustion chamber is further preferred, especially in an annular combustion chamber, a gas turbine carried out.
- FIG. 1 shows a longitudinal section through an annular combustion chamber 1 for a gas turbine.
- the ring combustion chamber 1 is rotationally symmetrical around an axis 2. For the sake of clarity only half of the longitudinal section is shown.
- the ring combustion chamber 1 has a combustion chamber wall 3.
- the combustion chamber wall 3 encloses an annular space 4.
- the inner wall of the combustion chamber wall 3 is lined with an inner lining 5.
- the inner lining 5 is made by a variety of heat shield elements 6 formed.
- Such heat shield elements 6 are e.g. made of fireproof ceramic.
- Burner system 7 This is formed by a diffusion burner 8 and a premix burner 9, which is the diffusion burner 8 surrounds in the form of an annular channel.
- the burner system 7 is at a burner end 11 of the annular combustion chamber 1 arranged. At an opposite end 11 of the burner turbine-side end 13 closes one schematically shown gas turbine 15.
- the gas turbine system When using such an annular combustion chamber 1 in one here
- the gas turbine system is the pilot burner 8 Fuel 17A supplied.
- the pilot burner 8 is also Combustion air 18A supplied.
- the fuel 17A and the Combustion air 18A are diffused through the Pilot burner 8 burned in the annular space 4 of the annular combustion chamber 1.
- On the flame stabilized on the pilot burner 8 Combustion ignites a mixture of fuel 17B and Combustion air 18B, which is fed to the premix burner 9 becomes.
- the exhaust gas 20 generated by the combustion emerges the turbine-side end 13 of the annular combustion chamber 1 and drives the gas turbine 15.
- FIG 2 shows a section of a corresponding to Figure 1 Longitudinal section through an annular combustion chamber 1.
- One of the Heat shield elements 6 is as a burner heat shield element 22 executed. Like each of the heat shield elements 6 is also the burner heat shield element 22 with a screw 24 the combustion chamber wall 3 screwed. In the combustion chamber wall 3 22 holes are behind the burner heat shield element 26 provided. On the outside 28 of the combustion chamber wall 3 a fuel line 30 is also provided. Of the Fuel line 30 leads through hole 32 of the combustion chamber wall 3 to a pre-mixing space 34, which by the at the Combustion chamber wall 3 adjacent burner heat shield element 22 is formed. The through holes also open into the premixing chamber 34 26.
- the burner heat shield element 22 extends from a first end 23 to a second end 25.
- the burner heat shield element 22 is now in the following manner for a second stage of combustion in the annular combustion chamber 1 used:
- Fuel 36 is preferred via fuel line 30 Natural gas, the premixing chamber 34 is supplied via the bore 32. Combustion air 38 is also passed through the perforations 26 fed to the premixing chamber 34. In the premixing room 34 the natural gas 36 mixes with the combustion air 38. Am second end 25, an outlet opening 40 is provided which Natural gas-air mixture 42 discharges into the annular combustion chamber 1. The Natural gas-air mixture 42 ignites in the hot annular combustion chamber 1. This creates a second stage of combustion out. With this second stage, the reaction zone the combustion occurring in the annular combustion chamber 1 is increased. This leads to a reduced tendency to training of combustion vibrations. The significant combustion air flow 38 continues to result in high cooling performance for the burner heat shield element 22 and also for the downstream side located in front of the burner heat shield element 22 further heat shield elements 6.
- Figure 3 shows again in an enlarged and schematic Representation of a arranged on the burner chamber wall 3 Burner heat shield element 22.
- a burner heat shield element is shown schematically in a longitudinal section in FIG 22 shown, which on a combustion chamber wall 3 is arranged.
- the burner heat shield element 22 is formed from a porous material 44. It is with brackets 46 attached to the combustion chamber wall 3.
- brackets 46 attached to the combustion chamber wall 3.
- a fuel line 30 is integrated into the wall 48. Openings 50 are also provided in the wall 48.
- the premixing chamber 34 is fluidically connected to the Burner heat shield element 22 through holes 26 in the Combustion chamber wall 3 connected.
- Combustion air 38 enters the premixing chamber via the openings 50 34.
- Fuel comes from the fuel line 30, preferably natural gas, also in the premixing chamber 34.
- the fuel-air mixture passes through the through holes 26 42 from the premixing chamber 34 into the burner heat shield element 22.
- the fuel-air mixture 42 penetrates into the porous Material 44 a. Due to the heat in one, no further
- the combustion chamber shown ignites the fuel-air mixture 42 and burns within the pores of the porous material 44.
- the porous material 44 heats up. This leads to a particularly stable combustion.
- a combustion vibration due to the pore structure of the porous material 44 suppressed.
- the porous continues to shine Material 44 heat. This leads to the flame temperature the combustion within the porous material 44 by comparison is low. This in turn has the consequence that less nitrogen oxides are formed.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
Description
- FIG 1
- ein Längsschnitt durch eine Ringbrennkammer einer Gasturbine,
- FIG 2
- einen vergrößerten Ausschnitt aus einer Ringbrennkammer mit einem Brenner-Hitzeschildelement,
- FIG 3
- ein Brenner-Hitzeschildelement und
- FIG 4
- ein Brenner-Hitzeschildelement aus einem porösen Material.
Claims (12)
- Brennkammer (1) mit einer einen Brennraum (4) umschließenden Brennkammerwand (3) und mit einer aus einer Vielzahl von Hitzeschildelementen (6) gebildeten Innenauskleidung (5) ,
dadurch gekennzeichnet, daß mindestens ein als Brenner fungierendes Hitzeschildelement (5) ein Brenner-Hitzeschildelement (22) ist, dem eine Brennstoffzuführung (30) für Brennstoff (36) und eine Verbrennungsluftzuführung (26) für Verbrennungsluft (38) vorgeschaltet sind, und, daß das Brenner-Hitzeschildelement (22) ein mit zahlreichen Hohlräumen (45) versehenes Material (44) aufweist, welches so ausgebildet ist, daß eine Verbrennung innerhalb dieses Materials (44) erzeugbar ist aus gestrichener Anspruch 6 einsetzer. - Brennkammer (1) nach Anspruch 1,
dadurch gekennzeichnet, daß dem Brenner-Hitzeschildelement (22) ein Vormischraum (34) vorgeschaltet ist, in den der Brennstoff (36) und die Verbrennungsluft (38) einleitbar sind. - Brennkammer (1) nach Anspruch 2,
dadurch gekennzeichnet, daß die Brennkammerwand (3) eine Außenseite (28) aufweist, entlang der sich die Brennstoffzuführung (30) erstreckt. - Brennkammer (1) nach einem der vorhergehenden Ansprüche, durch die entlang einer Ausdehnungsrichtung ein Brenngasstrom (20) von einer Eintrittsseite (11) bis zu einer Austrittsseite (13) führbar ist, wobei mindestens ein Brenner (8) für eine erste Stufe einer Verbrennung vorgesehen ist,
dadurch gekennzeichnet, daß durch das Brenner-Hitzeschildelement (22) stromab der ersten Stufe eine zweite Stufe der Verbrennung erzeugbar ist. - Brennkammer (1) nach Anspruch 2 und 4,
dadurch gekennzeichnet, daß der Vormischraum (34) zwischen der Brennkammerwand (3) und dem Brenner-Hitzeschildelement (22) angeordnet ist, wobei das Brenner-Hitzeschildelement (22) sich entlang der Ausdehnungsrichtung von einem ersten Ende (23) bis zu einem zweiten Ence (25) erstreckt und wobei in Bereich des zweiten Endes (25) eine Auslaßöffnung (40) den Vormischraum (34) mit dem Brennraum (4) verbindet. - Brennkammer (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß das Matarial (44) des Brenner-Hitzeschildelements (22) Metall ist, in welches mechanisch, insbesondere durch Bohren, die Kohlräume (45) eingebracht sind. - Brennkammer (1) nach einem der Ansprüche 1 bis 5,
dadurch gekennzeichnet, daß das Material (44) des Brenner-Hitzeschildelements (22) eine poröse Keramik, insbesondere Zirkonoxid oder Siliziumcarbid, ist. - Brennkammer (1), insbesondere Ringbrennkammer, nach einem der vorhergehenden Ansprüche, bei der der Brennraum (4) ringförmig ausgebildet ist,
dadurch gekennzeichnet, daß entlang einer Umfangsrichtung des Ringraumes (4) eine Mehrzahl von Hitzeschildelementen (6) als Brenner-Hitzeschildelemente (22) ausgebildet sind. - Verwendung einer Brennkammer (1) nach einem der vorhergehenden Ansprüche für eine Gasturbine, insbesondere für eine stationäre Gasturbine mit einer Leistung größer als 60 MW.
- Verfahren zum Betrieb einer Brennkammer (1) mit einer Brennkammerwand (3) und mit einer aus einer Vielzahl von Hitzeschildelementen (6, 22) gebildeten Innenauskleidung (5), dadurch gekennzeichnet, daß mindestens einem der Hitzeschildelemente (6, 22) Brennstoff (36) un d Verbrennungsluft (38) für eine Verbrennung (1) zugeführt werden, und daß der Brennstoff (36) und die Verbrennungsluft (38) innerhalb eines porösen Materials (44) des Hitzeschildelementes (22) verbrannt werden.
- Verfahren nach Anspruch 10,
dadurch gekennzeichnet, daß zunächst eine erste Stufe einer Verbrennung abläuft und anschließend über das Hitzeschildelement (22) eine zweite Stufe der Verbrennung erfolgt. - Durchführung des Verfahrens nach einem der Ansprüche 10 oder 11 in einer Brennkammer (1), insbesondere in einer Ringbrennkammer, einer Gasturbine.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19810276 | 1998-03-10 | ||
DE19810276 | 1998-03-10 | ||
PCT/DE1999/000513 WO1999046540A1 (de) | 1998-03-10 | 1999-02-25 | Brennkammer und verfahren zum betrieb einer brennkammer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1062461A1 EP1062461A1 (de) | 2000-12-27 |
EP1062461B1 true EP1062461B1 (de) | 2003-12-03 |
Family
ID=7860355
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99913091A Expired - Lifetime EP1062461B1 (de) | 1998-03-10 | 1999-02-25 | Brennkammer und verfahren zum betrieb einer brennkammer |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP1062461B1 (de) |
JP (1) | JP4365027B2 (de) |
DE (1) | DE59907940D1 (de) |
WO (1) | WO1999046540A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7029272B2 (en) | 2001-08-09 | 2006-04-18 | Siemens Aktiengesellschaft | Premix burner and method for operation thereof |
WO2018202407A1 (de) | 2017-05-04 | 2018-11-08 | Siemens Aktiengesellschaft | Brennkammer |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4524902B2 (ja) * | 2000-10-25 | 2010-08-18 | 株式会社Ihi | 予混合燃料噴射弁を備えた低NOx燃焼器 |
EP1460339A1 (de) * | 2003-03-21 | 2004-09-22 | Siemens Aktiengesellschaft | Gasturbine |
EP1557607B1 (de) * | 2004-01-21 | 2010-09-29 | Siemens Aktiengesellschaft | Brenner mit gekühltem Bauteil, Gasturbine sowie Verfahren zur Kühlung des Bauteils |
EP1847696A1 (de) * | 2006-04-21 | 2007-10-24 | Siemens Aktiengesellschaft | Bauteil für eine gestufte Verbrennung in einer Gasturbine und entsprechende Gasturbine. |
EP1847684A1 (de) | 2006-04-21 | 2007-10-24 | Siemens Aktiengesellschaft | Turbinenschaufel |
US8800293B2 (en) * | 2007-07-10 | 2014-08-12 | United Technologies Corporation | Floatwell panel assemblies and related systems |
EP2161500A1 (de) | 2008-09-04 | 2010-03-10 | Siemens Aktiengesellschaft | Verbrennungssystem und Verfahren zur Verringerung der Verbrennungsinstabilität und/oder Emissionen eines Verbrennungssystems |
WO2019172925A2 (en) * | 2018-03-09 | 2019-09-12 | Siemens Aktiengesellschaft | Finely distributed combustion system for a gas turbine engine |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE253189C (de) * | ||||
BE790956A (fr) * | 1971-11-05 | 1973-03-01 | Penny Robert N | Tube de flamme pour chambre de combustion de moteur a turbine agaz |
US3981675A (en) * | 1974-12-19 | 1976-09-21 | United Technologies Corporation | Ceramic burner construction |
US4112676A (en) * | 1977-04-05 | 1978-09-12 | Westinghouse Electric Corp. | Hybrid combustor with staged injection of pre-mixed fuel |
US4910957A (en) * | 1988-07-13 | 1990-03-27 | Prutech Ii | Staged lean premix low nox hot wall gas turbine combustor with improved turndown capability |
FR2647534B1 (fr) * | 1989-05-29 | 1991-09-13 | Europ Propulsion | Chambre de reacteur et procede pour sa fabrication |
DE59208831D1 (de) | 1992-06-29 | 1997-10-02 | Abb Research Ltd | Brennkammer einer Gasturbine |
EP0597137B1 (de) | 1992-11-09 | 1997-07-16 | Asea Brown Boveri AG | Gasturbinen-Brennkammer |
JP3404981B2 (ja) * | 1995-04-21 | 2003-05-12 | 日本鋼管株式会社 | 気体加熱装置 |
-
1999
- 1999-02-25 EP EP99913091A patent/EP1062461B1/de not_active Expired - Lifetime
- 1999-02-25 WO PCT/DE1999/000513 patent/WO1999046540A1/de active IP Right Grant
- 1999-02-25 DE DE59907940T patent/DE59907940D1/de not_active Expired - Lifetime
- 1999-02-25 JP JP2000535877A patent/JP4365027B2/ja not_active Expired - Fee Related
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7029272B2 (en) | 2001-08-09 | 2006-04-18 | Siemens Aktiengesellschaft | Premix burner and method for operation thereof |
WO2018202407A1 (de) | 2017-05-04 | 2018-11-08 | Siemens Aktiengesellschaft | Brennkammer |
DE102017207487A1 (de) * | 2017-05-04 | 2018-11-08 | Siemens Aktiengesellschaft | Brennkammer |
Also Published As
Publication number | Publication date |
---|---|
JP4365027B2 (ja) | 2009-11-18 |
DE59907940D1 (de) | 2004-01-15 |
WO1999046540A1 (de) | 1999-09-16 |
JP2002506193A (ja) | 2002-02-26 |
EP1062461A1 (de) | 2000-12-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0576697B1 (de) | Brennkammer einer Gasturbine | |
DE69719688T2 (de) | Gasturbinenbrenner und Betriebsverfahren dafür | |
DE3854666T2 (de) | Gasturbinenbrenner. | |
EP1064498B1 (de) | Gasturbinenbrenner | |
EP1336800B1 (de) | Verfahren zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen sowie Vormischbrenner zur Durchführung des Verfahrens | |
DE60224141T2 (de) | Gasturbine und Brennkammer dafür | |
EP0193838B1 (de) | Brenneranordnung für Feuerungsanlagen, insbesondere für Brennkammern von Gasturbinenanlagen sowie Verfahren zu ihrem Betrieb | |
DE60007946T2 (de) | Eine Brennkammer | |
EP0710797B1 (de) | Verfahren und Vorrichtung zum Betrieb eines Vormischbrenners | |
EP1654496B1 (de) | Brenner und verfahren zum betrieb einer gasturbine | |
EP1754002B1 (de) | Gestufter vormischbrenner mit einem injektor für flüssigbrennstoff | |
DE10064259B4 (de) | Brenner mit hoher Flammenstabilität | |
DE4446842B4 (de) | Verfahren und Vorrichtung zum Zuleiten eines gasförmigen Brennstoffs in einen Vormischbrenner | |
EP0274630A1 (de) | Brenneranordnung | |
DE10050248A1 (de) | Brenner | |
EP1950494A1 (de) | Brennkammer für eine Gasturbine | |
EP0687860A2 (de) | Brennkammer mit Selbstzündung | |
EP1062461B1 (de) | Brennkammer und verfahren zum betrieb einer brennkammer | |
EP0363834A1 (de) | Brenner, insbesondere Hochgeschwindigkeitsbrenner | |
EP0995066B1 (de) | Brenneranordnung für eine feuerungsanlage, insbesondere eine gasturbinenbrennkammer | |
WO2012016748A2 (de) | Gasturbinenbrennkammer | |
DE102005061486A1 (de) | Brennkammer mit Brenner und zugehöriges Betriebsverfahren | |
EP0727611A1 (de) | Brennkammer mit Zweistufenverbrennung | |
EP1555484B1 (de) | Verfahren zum Betreiben einer Gasturbinen-Brennkammer | |
EP2191200B1 (de) | Vormischstufe für einen gasturbinenbrenner |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20000821 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): CH DE FR GB IT LI |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE FR GB IT LI |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: SERVOPATENT GMBH Ref country code: CH Ref legal event code: EP |
|
REF | Corresponds to: |
Ref document number: 59907940 Country of ref document: DE Date of ref document: 20040115 Kind code of ref document: P |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20040310 |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20040906 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PCAR Free format text: SIEMENS SCHWEIZ AG;INTELLECTUAL PROPERTY FREILAGERSTRASSE 40;8047 ZUERICH (CH) |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20100225 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20120222 Year of fee payment: 14 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20130301 Year of fee payment: 15 Ref country code: GB Payment date: 20130213 Year of fee payment: 15 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20130419 Year of fee payment: 15 Ref country code: CH Payment date: 20130510 Year of fee payment: 15 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 59907940 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20140225 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140228 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140228 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20141031 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 59907940 Country of ref document: DE Effective date: 20140902 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140228 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140225 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140902 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140225 |