EP1614963A1 - Système de combustion à prémélange et procédé - Google Patents

Système de combustion à prémélange et procédé Download PDF

Info

Publication number
EP1614963A1
EP1614963A1 EP20040016247 EP04016247A EP1614963A1 EP 1614963 A1 EP1614963 A1 EP 1614963A1 EP 20040016247 EP20040016247 EP 20040016247 EP 04016247 A EP04016247 A EP 04016247A EP 1614963 A1 EP1614963 A1 EP 1614963A1
Authority
EP
European Patent Office
Prior art keywords
fuel
mixture
air
mixing
premix
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Withdrawn
Application number
EP20040016247
Other languages
German (de)
English (en)
Inventor
Andreas Heilos
Bernd Dr. Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP20040016247 priority Critical patent/EP1614963A1/fr
Publication of EP1614963A1 publication Critical patent/EP1614963A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • 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
    • 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

Definitions

  • the invention relates to a method for combustion of a fuel for the operation of a gas turbine, in which the fuel is premixed with air in a premix to a fuel-air mixture and in the context of combustion, the fuel-air mixture is converted into a hot gas ,
  • the invention also relates to a premix combustion system having a pre-mixing chamber and a combustion chamber.
  • a gas turbine is an engine that converts the heat energy of a hot gas into mechanical energy.
  • Gas turbines are used in the art as drive units, for example for the production of electric power.
  • Under a gas turbine plant is generally understood not only the gas turbine itself, but an aggregate of various components. These include, among others, the components connected in series, compressor, combustion chamber, turbine and generator.
  • the compressed air flows behind the compressor to a combustion chamber, which with several burners, the air by combustion of a fuel, for. B. in the form of a fuel gas or in the form of fuel oil, in modern machines to a temperature of about 1400 ° C, heated.
  • a fuel gas for. B. in the form of natural gas or synthesis gas (main components CO, H 2 and possibly secondary components, such as N 2 , CO 2 , water vapor).
  • the hot gas usually flows from the combustion chamber into the gas turbine and is relaxed there by driving a rotor.
  • the axially exiting exhaust gases from the gas turbine pass through an exhaust duct into a waste heat boiler or directly in a fireplace.
  • driving machines eg. As a generator, the difference is the output from the gas turbine power minus the power supplied to the compressor available.
  • the aim of an embodiment of a gas turbine is, in addition to the highest possible efficiency, a low nitrogen oxide emission with respect to the exhaust gases that are produced during the combustion of the fuel (NO x emission).
  • Burning is known according to the principle of the diffusion flame.
  • a particularly homogeneous combustion is achieved because the flame front of the diffusion flame substantially, depending on the progress of a mixture of a fuel with air to a fuel-air mixture adjusted such that it preferably in the range of a near-stoichiometric composition of a fuel-air -Gemisches burns.
  • This leads to peak temperatures in a diffusion flame which is typical for combustion with diffusion flames.
  • a peak temperature can be well over 1800 ° C, possibly up to 2400 ° C.
  • This peak temperature is achieved in diffusion flames because the flame front automatically adjusts itself where the most favorable combustion conditions corresponding to the stoichiometry of the fuel-air mixture are present.
  • the flame front typically stabilizes in diffusion flames at the positions where the fuel-air mixture reaches near-stoichiometric level due to the highest reactivity present at near-stoichiometric mixture.
  • diffusion flames burn very stably in the reaction zone due to the maximum reactivity which can be achieved by the fuel, but on the other hand diffusion flames also cause a high nitrogen oxide emission.
  • the nitrogen oxide emission increases exponentially with the flame temperature.
  • temperatures below 1600 ° C are technologically meaningful. All overlying temperatures, especially local peak temperatures, such. B. particularly pronounced in a diffusion flame, only increase the component load and NO x emission.
  • the aim of a design of a combustion system and a method for combustion of a fuel for the operation of a gas turbine is thus to adjust a turbine temperature with respect to the thermodynamic and material-related requirements of the gas turbine plant while avoiding peak temperatures.
  • premix combustion For nitrogen oxide-poor combustion of hydrocarbons, the principle of premix combustion has been successfully used in gas turbines for many years.
  • the aim of the pre-mixed combustion is to provide a need-based mixing of fuel with air to a fuel-air mixture as part of a premix.
  • a lean premix a fuel-air mixture with excess air (ie with an air ratio greater than one). That is, in terms of a stoichiometric ratio for the computationally complete oxidizing reaction of the fuel to oxidation products CO 2 and H 2 O is a lean premix a fuel-air mixture is provided in which the air is more than stoichiometric, that is stoichiometrically less fuel can be oxidized by the oxygen contained in the air. Since air is admixed beyond a stoichiometric mixed state in the lean premix, additional ballast air is present, which must be co-heated in a combustion. The achievable combustion temperature depends on the amount of excess air or the air ratio.
  • a lean premix flame Compared to a superstoichiometric diffusion flame, a lean premix flame has the advantage of avoiding the peak temperature occurring in superstoichiometric diffusion flames. In contrast, the lean premix combustion inherently has a lower flame stability compared to flame extinction since the reactivity is limited to the level given in the lean premix.
  • No. 6,358,040 describes an apparatus in which a stepped mixture takes place.
  • the mixture produced after the first mixing stage is defined partially converted to a catalyst to ensure stabilization of a homogeneous reaction without aerodynamic stabilization after a second mixing stage.
  • This type of premix thus already provides for a partial catalytic conversion of the rich fuel-air mixture, so that a catalytic reactor can be operated protected against overheating under rich mixture conditions.
  • lean premix combustion is again achieved for complete burnout to a hot gas.
  • the invention begins, whose task is to provide a method and apparatus for combustion of a fuel for the operation of a gas turbine, in which ignition of a fuel-air mixture is safely avoided and wherein a particularly low nitrogen oxide emission in the Combustion is achieved.
  • this object is achieved by an aforementioned method in which according to the invention in the premix, a reaction of a fuel-air mixture is avoided and the premix is gradual, being produced as part of a first mixture, a rich fuel-air mixture and mixing the rich fuel-air mixture with air as part of a second mixture.
  • the invention is based on the consideration that usually provided in technical Vormischverbrennungssystemeen mixing path is limited, so that neither critical auto-ignition times are exceeded nor a flashback of the flames can be done.
  • the invention is based on the finding that an extension of the mixing path or the mixing time can be achieved without increasing the risks mentioned above, if the mixing process is graded so that in a first mixing stage, a still fuel-rich mixture is produced, not due to its composition or only a little at risk of ignition.
  • This mixing process to the rich mixture is then not subject to a limitation of the technical mixing way for the reasons mentioned above. A corresponding limitation may only be necessary for the second mixing stage.
  • the invention is further based on the consideration that previously known Vormischverbrenn Heidelberg, as far as they provide a gradual mixture, already imply a deliberate or an unwanted implementation or ignition of a fuel-air mixture.
  • US Pat. No. 6,358,040 proposes to pre-ignite the rich fuel-air mixture produced in a first mixing stage as part of a stepped premix.
  • the possible bandwidth of the mixture composition in this first mixing stage is limited such that, as a result of the catalytically initiated reaction, the maximum temperatures of the materials used are not exceeded.
  • the possible bandwidth of the mixture in the first mixing stage is further limited than required in the direction of smaller amounts of admixed air, whereby the potential for achieving the most homogeneous possible mixing at the end of the second mixing stage is limited contrary to the objective.
  • the finding of the present invention is that in the premix, a reaction of a fuel-air mixture is avoided. Furthermore, the gradation of the premix avoids the risk of autoignition and / or kickback until sufficient mixing of the fuel with the air to form a fuel / air mixture has taken place and has led to a very good, homogeneous and substoichiometric fat fuel-air mixture. Such a rich fuel-air mixture can therefore be generated safely and homogeneously in a first mixture, ie in a mixing stage. As part of a second mixture, the rich fuel-air mixture is mixed with the remaining combustion air. The ratio of the proportions to be mixed in comparison to a usual complete mixing of the fuel in a mixing stage in the total air is much more balanced. As a result of the comparatively safe and good mixture, a large nitrogen oxide reduction potential is achieved in comparison with advanced methods of a conventional type, for example US Pat. No. 6,358,040, which is limited in principle only by the physical limit of perfect premix combustion.
  • a first fraction of an air stream is mixed with a total fuel stream or with a first fraction of a fuel stream.
  • the first fraction of the air flow is so small that an air ratio less than one, so a stoichiometric, rich fuel-air mixture is provided.
  • a second fraction of an air stream is expediently mixed with the rich fuel-air mixture.
  • the air ratio of the rich fuel-air mixture can be adjusted particularly well. In particular, this makes possible a sufficiently long mixing of fuel with air without the risk of auto-ignition of the fuel-air mixture within the premix.
  • the second fraction of the air flow and the rich fuel-air mixture is supplied via a formed by a plurality of alternating currents flow cross-section of the second mixture. That is, the second fraction of the airflow is split into a plurality of streams.
  • the rich fuel-air mixture is divided into a plurality of streams. With an alternating arrangement over the flow cross section of the air streams on the one hand and the rich fuel-air mixture streams on the other hand, thus the second mixture is introduced.
  • the currents are thus arranged alternately, wherein preferably an air flow of a fuel-air mixture stream is adjacent and different currents are thus arranged alternately over the cross section.
  • a limited residence time of the second fraction of the air flow with the rich fuel-air mixture is set in the second mixture, preferably regulated. This can improve the fuel-air mixture in the premix.
  • the fuel-air mixture is converted to a hot gas after completion of the second mixture in the context of combustion.
  • further mixtures could follow the example of the second mixture. It has been found in the present case that, in particular in the context of the refinements explained above, a particularly even with the second mixture homogeneous and good stoichiometric fat burning fuel-air mixture can be achieved.
  • the conditions for the stability of the combustion after the second mixing stage can be improved by a pretreatment of the air and / or the fuel.
  • the air is lifted regulated to a first temperature level.
  • the reactivity of the fuel-air mixture after the second mixture is controlled so increased that a stable combustion is achieved.
  • the temperature should remain below the permissible temperature for the materials used.
  • it should be so low that the reactivity in the second mixture safely avoids a flashback. This can be compensated for by limiting the residence time in the second mixture. The lower the residence time is set in the second mixing stage, the lower the risk of flashback.
  • an increase in the temperature can be achieved in different ways depending on the design of the method.
  • a part of the hot gas can be recycled as exhaust gas flow to the premix.
  • the exhaust gas stream may be mixed with a second fraction of an air stream.
  • the exhaust gas stream is mixed before the actual premix with the second fraction of the air flow.
  • a second fraction of a fuel stream it has also proved to be advantageous for a second fraction of a fuel stream to be mixed with a second fraction of an air stream.
  • the combustion of the fuel stream is provided before the actual premix, ie a pilot combustion, which in turn may be advantageously carried out as Vormischverbrennung.
  • Both the exhaust gas recirculation and a pilot combustion of a second fraction of a fuel stream can advantageously be carried out individually or in combination before an actual premixing with the air stream, so that the air is controlled to a first temperature level for premixing.
  • the object is achieved by a premix combustion system of the type mentioned for combustion of a fuel for the operation of a gas turbine.
  • the premix space is provided for premixing the fuel with air to a fuel-air mixture.
  • the combustion chamber is provided for combustion of the fuel-air mixture to a hot gas.
  • the premixing chamber in the premix combustion system, has a multi-stage design, with a first mixing stage and a second mixing stage.
  • this is advantageous in order to avoid an undesired ignition of the fuel-air mixture within the mixing chambers of the mixing stages with nevertheless a large mixing time.
  • the first mixing stage serves to produce a rich fuel-air mixture.
  • the second mixing stage serves to mix the rich fuel-air mixture with air.
  • premix combustion system is used in particular for carrying out the method explained above.
  • advantages explained with regard to the method can also be realized in particular in the premix combustion system.
  • a central design feature of a premix burner in a further development relates in particular to Realization of the best possible spatial and temporal mixture and thus optimization of the nitrogen oxide lowering potential.
  • the first mixing stage is provided with a mixing zone providing a mixing length of between 30 cm and 50 cm, preferably about 40 cm.
  • a particularly good mixture of the rich fuel-air mixture can be achieved as part of a premix.
  • the second mixing stage is provided with a mixing nozzle assembly having a flow area formed by a plurality of parallel channels.
  • the plurality of channels serves in particular for receiving a plurality of alternating currents according to a development of the method explained above.
  • the second mixing stage has a nozzle plate which is arranged between the mixing nozzle arrangement and a second mixing zone.
  • the second mixing stage is also provided with a mixing zone which is available with a mixing length in the range of 10 cm to 30 cm, preferably about 20 cm.
  • a mixing length in the range of 10 cm to 30 cm, preferably about 20 cm.
  • the Vormischverbrennungssystem can be provided with a number of additional design measures.
  • an exhaust gas recirculation emanating from the combustion chamber is provided in order to recirculate part of the hot gas as exhaust gas flow to the premix.
  • the premix combustion system has a pilot space.
  • the exhaust gas recirculation discharges into the pilot space. In this way, namely, an exhaust gas stream can be mixed with a second fraction of an air stream.
  • the pilot space has a pilot burner. This piloting is particularly suitable for realizing a stable premix combustion after the second mixing stage.
  • a swirl generator can be provided between the second mixing stage and the combustion chamber for this purpose.
  • the twisting of a burner flame leads to the induction of an internal remindströmzone to an aerodynamic stabilization of the flame. In particular, blowing away the flame from the burner is avoided.
  • baffle plate between the second mixing stage and the combustion chamber. This causes a separation vortices on the edge and behind the baffle plate and a corresponding negative pressure situation behind the baffle plate, which in turn leads to a retention the flame and thus an aerodynamic stabilization of the flame leads.
  • the invention also leads to a gas turbine plant with a premix combustion system as explained above.
  • the premix combustion system 10 has a pre-mixing space 1, which in the present case has a multi-stage design.
  • the multi-stage premixing chamber 1 has a first mixing stage 3 and a second mixing stage 5.
  • the premixing space serves to premix fuel B with air L to form a fuel-air mixture BL.
  • a rich fuel-air mixture BL is generated in the present preferred embodiment.
  • the second mixing stage 5 is under a second mixture, the rich fuel-air mixture BL mixed with air L.
  • a first fraction M_L1 with a first fraction of a fuel flow M_B1 is provided for the first mixture in the first mixing stage 3.
  • the mixture takes place in particular in a first mixing zone 7 of the first mixing stage 3 over a mixing length of about 40 cm.
  • At the end of the mixing zone 7 is thus achieved a particularly high degree of mixedness for the fuel-air mixture BL in terms of homogeneity.
  • the presently cylindrical premix combustion system 10 has a cylindrically designed premixing chamber 1 with a ring-cylindrical first mixing stage 3 and a correspondingly cylindrical mixing stage 5.
  • air L is mixed with the rich fuel-air mixture BL.
  • the particularly preferred embodiment of a premix combustion system 10 having a premix space 1 provides the air L thereto via a pilot space 9.
  • the pilot space 9 has a pilot burner 11, via which the air L is supplied as a second fraction of an air flow M_L2.
  • a second fraction of a fuel flow M_B2 is converted in the pilot burner 11 together with a second fraction of an air flow M_L2.
  • an exhaust gas recirculation system 15 branching off from a combustion chamber 13 discharges into the pilot chamber 9 and supplies the pilot chamber 9 with hot gas H from the combustion chamber 13.
  • the plurality of channels 19A carries a plurality of alternating flows.
  • the channels 19A carry a stream of the rich fuel-air mixture BL from the first mixing stage 3.
  • the intermediate channels 19B carry a stream of exhaust A, fuel B and air L, which are supplied from the pilot space 9.
  • the output-side outlets of the channels 19A, 19B lead the now alternately adjacent streams of the rich fuel-air mixture BL on the one hand and the air L, the fuel B and the exhaust A on the other hand to a nozzle plate 21, with an already good mixture of the rich fuel-air mixture BL and the air L (with fuel B and exhaust gas A) of a second mixing zone 23 of the second mixing stage 5 is supplied as part of an injection 25.
  • the injection takes place at an already elevated temperature level T 2 .
  • the air is namely raised in the pilot chamber 9 to the first temperature level T 1 , by supplying hot gas in the form of exhaust gas A via the exhaust gas recirculation 15.
  • a pilot burner 11 is provided for implementing a second fuel flow M_B2 with a second fraction of an air flow M_L2.
  • the spatial mixture is achieved, inter alia, by the mixing nozzle arrangement 17 explained above.
  • a particularly good temporal mixture is established.
  • a second mixing zone 23 of the second mixing stage 5 is selected so that a sufficient residence time t of to be burnt mixture G is achieved.
  • the residence time t in the second mixing stage 5 is limited such that self-ignition of the mixture G to be combusted is still avoided in the second mixing stage 5. This applies analogously to the temperature level with temperature T 2 of the mixture G in the second mixing stage 5.
  • both a mixing length of a first mixing zone 7 and a mixing length of a second mixing zone 23 can be chosen to be much greater than in conventional premixing spaces the case would be.
  • the mixing length of a mixing zone 23 of a second mixing stage 5 in the present embodiment is less than about 20 cm.
  • the mixture G to be combusted has a sufficient mixture, so that it can be supplied to the combustion chamber 13 via a swirl generator 27.
  • a swirl generator 27 serves to stabilize the flame F.
  • a higher pressure level is generated due to the swirl in the outer region of the flame F.
  • the lower pressure level prevailing in the interior of the flame prevents the flame F from being blown away from the burner.
  • FIG. 2 shows a preferred module 20 of a mixing nozzle arrangement 17, which is explained in more detail in FIG.
  • the module 20 forms part of a flow cross-section 29 and carries a plurality of alternating streams 18A and 18B which are guided in a respective channel 19A and 19B.
  • a channel 19A carries a rich fuel-air mixture BL in a flow 18A.
  • a channel 19B carries portions of a pilot space 9, the mixture of air L, fuel B and exhaust gas A.
  • the module 20, with its channels 19A, 19B, is a non-catalytic module designed solely for advantageous mixing and does not provide any catalytic activity.
  • the module 20 has a hexagonal shape 31.
  • the module 20 is particularly preferably designed for execution with a tube bundle for the alternating distribution of air and rich mixture.
  • a method which provides, as part of a premix, to premix the fuel B with air L to form a fuel-air mixture BL and during combustion to convert the fuel-air mixture BL to a hot gas H.
  • a conversion of a fuel-air mixture BL is avoided within the mixing stages and the premixing takes place stepwise, wherein in a first mixture, a rich fuel-air mixture BL is generated and in a second mixture rich fuel-air mixture BL with air L, in particular to a lean mixture, is mixed.
  • a premix combustion system 10 for combusting a fuel B for the operation of a gas turbine provides a premixing chamber 1 and a combustion chamber 13 in which, according to the proposed concept, the premixing chamber 1 is designed in multiple stages, with a first mixing stage 3 and a second mixing stage 5.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP20040016247 2004-07-09 2004-07-09 Système de combustion à prémélange et procédé Withdrawn EP1614963A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20040016247 EP1614963A1 (fr) 2004-07-09 2004-07-09 Système de combustion à prémélange et procédé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20040016247 EP1614963A1 (fr) 2004-07-09 2004-07-09 Système de combustion à prémélange et procédé

Publications (1)

Publication Number Publication Date
EP1614963A1 true EP1614963A1 (fr) 2006-01-11

Family

ID=34925693

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20040016247 Withdrawn EP1614963A1 (fr) 2004-07-09 2004-07-09 Système de combustion à prémélange et procédé

Country Status (1)

Country Link
EP (1) EP1614963A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014133406A1 (fr) * 2013-02-28 2014-09-04 General Electric Company Système et procédé pour une chambre de combustion de turbine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0059490A1 (fr) * 1981-03-04 1982-09-08 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion annulaire avec brûleur annulaire pour turbines à gaz
EP0276096A1 (fr) 1987-01-21 1988-07-27 Mobil Oil Corporation Procédé de métathèse d'oléfine
EP0276696A2 (fr) * 1987-01-26 1988-08-03 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
EP0719983A1 (fr) * 1994-12-27 1996-07-03 ABB Management AG Procédé et dispositif d'alimentation du combustible gazeuse vers un brûleur à prémélange
EP0916894A1 (fr) * 1997-11-13 1999-05-19 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP1174662A1 (fr) * 2000-07-21 2002-01-23 Mitsubishi Heavy Industries, Ltd. Dispositif pour la réduction des vibrations dans une chambre de combustion de turbine
US6358040B1 (en) 2000-03-17 2002-03-19 Precision Combustion, Inc. Method and apparatus for a fuel-rich catalytic reactor
EP1217297A1 (fr) 2000-12-22 2002-06-26 ALSTOM Power N.V. Brûleur à stabilité de flamme élévée
EP1255080A1 (fr) * 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Brûleur catalytique
EP1279898A2 (fr) 2001-07-26 2003-01-29 ALSTOM (Switzerland) Ltd Brûleur à prémélange offrant une haute stabilité de flamme
WO2004020905A1 (fr) * 2002-08-30 2004-03-11 Alstom Technology Ltd Procede et dispositif pour faire bruler un melange combustible-oxydant

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0059490A1 (fr) * 1981-03-04 1982-09-08 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion annulaire avec brûleur annulaire pour turbines à gaz
EP0276096A1 (fr) 1987-01-21 1988-07-27 Mobil Oil Corporation Procédé de métathèse d'oléfine
EP0276696A2 (fr) * 1987-01-26 1988-08-03 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
EP0719983A1 (fr) * 1994-12-27 1996-07-03 ABB Management AG Procédé et dispositif d'alimentation du combustible gazeuse vers un brûleur à prémélange
EP0916894A1 (fr) * 1997-11-13 1999-05-19 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6358040B1 (en) 2000-03-17 2002-03-19 Precision Combustion, Inc. Method and apparatus for a fuel-rich catalytic reactor
EP1174662A1 (fr) * 2000-07-21 2002-01-23 Mitsubishi Heavy Industries, Ltd. Dispositif pour la réduction des vibrations dans une chambre de combustion de turbine
EP1217297A1 (fr) 2000-12-22 2002-06-26 ALSTOM Power N.V. Brûleur à stabilité de flamme élévée
EP1255080A1 (fr) * 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Brûleur catalytique
EP1279898A2 (fr) 2001-07-26 2003-01-29 ALSTOM (Switzerland) Ltd Brûleur à prémélange offrant une haute stabilité de flamme
WO2004020905A1 (fr) * 2002-08-30 2004-03-11 Alstom Technology Ltd Procede et dispositif pour faire bruler un melange combustible-oxydant

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014133406A1 (fr) * 2013-02-28 2014-09-04 General Electric Company Système et procédé pour une chambre de combustion de turbine
RU2637609C2 (ru) * 2013-02-28 2017-12-05 Эксонмобил Апстрим Рисерч Компани Система и способ для камеры сгорания турбины
US10221762B2 (en) 2013-02-28 2019-03-05 General Electric Company System and method for a turbine combustor

Similar Documents

Publication Publication Date Title
EP1812756B1 (fr) Procede pour mettre en marche un bruleur
DE69828916T2 (de) Emissionsarmes Verbrennungssystem für Gasturbinentriebwerke
EP2115353B1 (fr) Chambre de combustion pour une turbine à gaz
DE19536836C2 (de) Verfahren zum Betrieb einer Kraftwerksanlage
EP0274630B1 (fr) Agencement pour un brûleur
EP0713058A1 (fr) Chambre de combustion à plusieurs étage
DE102004003816A1 (de) Brennkammer
EP0576697A1 (fr) Chambre de combustion pour turbine à gaz
DE19614001A1 (de) Brennkammer
EP1217297A1 (fr) Brûleur à stabilité de flamme élévée
EP1614967B1 (fr) Procédé et système de combustion à prémélange
EP0889289A2 (fr) Système de turbine à gaz
EP1754937B1 (fr) Tête de brûleur et procédé pour brûler du combustible
EP0193029A1 (fr) Chambre de combustion pour turbines à gaz
DE102005061486B4 (de) Verfahren zum Betreiben einer Brennkammer einer Gasturbine
WO2003029725A1 (fr) Procede de combustion destine notamment a un procede de production de courant electronique et/ou de chaleur
EP3421885B1 (fr) Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement
CH672366A5 (fr)
DE102013112162A1 (de) Mikromischerdüse
EP0602396A1 (fr) Générateur de chaleur pour processus industriel
EP0595026A1 (fr) Procédé pour une combustion à plusieurs étages dans des turbines à gaz
EP1614963A1 (fr) Système de combustion à prémélange et procédé
DE10337526B4 (de) Brenner und Verfahren zum Verbrennen von Gas in einem Ofen
EP3940293A1 (fr) Procédé de combustion étagée d'un combustible et tête de combustion
DE19542644B4 (de) Vormischverbrennung

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

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

17P Request for examination filed

Effective date: 20060206

AKX Designation fees paid

Designated state(s): DE FR GB IT NL

17Q First examination report despatched

Effective date: 20100806

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20170201