WO1998012478A1 - Verfahren und einrichtung zur verbrennung von brennstoff mit luft - Google Patents
Verfahren und einrichtung zur verbrennung von brennstoff mit luft Download PDFInfo
- Publication number
- WO1998012478A1 WO1998012478A1 PCT/DE1997/001881 DE9701881W WO9812478A1 WO 1998012478 A1 WO1998012478 A1 WO 1998012478A1 DE 9701881 W DE9701881 W DE 9701881W WO 9812478 A1 WO9812478 A1 WO 9812478A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- air
- burner
- burners
- combustion chamber
- fuel
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D23/00—Assemblies of two or more burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
- F23M20/005—Noise absorbing means
-
- 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
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
Definitions
- the invention relates to a method for the combustion of fuel with air in a combustion chamber, to which the air is supplied through at least one air inlet and the fuel through several burners, each burner having an associated delay time which corresponds to a time period after which a acoustic impulse in the combustion chamber causes a thermal impulse during the combustion of the fuel supplied via this burner.
- the invention also relates to a corresponding device for the combustion of fuel with air.
- the invention relates in particular to a method and a device of the type mentioned at the outset for use in a gas turbine, a gas turbine being a composite of a compressor for air, a combustion device comprising at least one combustion chamber for burning a fuel in the air to form a flue gas and a turbine in the true sense to relax the flue gas.
- the turbine can be of several parts, that is to say it can comprise a plurality of subtowers connected behind one another; the same applies to the compressor.
- the compressor is in particular a turbo compressor. As part of common practice, the turbine drives the compressor.
- the invention relates to the task of damping or avoiding acoustic vibrations in a combustion chamber, which vibrations are induced by the combustion and are known as “combustion vibrations”.
- combustion vibrations In many combustion chambers, both in combustion chambers in gas turbines and in the combustion chambers of boiler furnaces, industrial furnaces or other systems, unstable operating states occur under certain conditions that are clearly defined by the relevant thermodynamic operating parameters, such as air ratio and thermal power, and are characterized through correlated fluctuations in heat production during combustion and the static pressure m in the combustion chamber and / or parts of the system connected upstream and downstream. These fluctuations are expressed in that self-excited acoustic vibrations occur in the combustion chamber. In addition to increased noise pollution in the surroundings of the plant concerned, these acoustic vibrations cause increased mechanical and thermal stresses on the combustion chamber and other parts of the plant, which can lead to complete or partial failure in a very short time.
- premix burners in corresponding combustion chambers, which is accompanied by increasing demands with regard to combustion with the lowest possible pollutants, leads due to the higher reaction density achieved with a premix burner, the ignition more dependent on the chemical composition of the mixture to be burned than in a diffusion burner, and also towards one
- Diffusion burners reduced convective delay time within the flame formed to an increased tendency to form combustion vibrations.
- a combustion vibration is generally based on one
- a criterion can also be derived from the Rayleigh criterion, which relates the period of an acoustic oscillation for which the possibility of its occurrence is discussed to a "delay time" that characterizes a burner and its operation.
- This delay time is a time period after which causes an acoustic pulse in the combustion chamber to which the burner is connected, a thermal pulse when the fuel supplied via the burner is burned in relation to a stable oscillation present in the combustion chamber and a thermal oscillation caused by it through the burner
- the period of delay corresponds to a phase difference between the acoustic and the thermal oscillation, ie a periodic fluctuation in the energy conversion in the combustion caused by the burner.
- the delay time of a burner in a combustion chamber is composed of various summands, which can each be traced back to individual components of the system comprising the burner, combustion chamber and frame.
- the summands related to the burner and the combustion chamber are mainly determined by the geometry of the burner and the combustion chamber; a summand that can be traced back to the flame itself is essentially determined by the properties of the combustion itself.
- the summand itself can be further broken down into a "convective delay time", which characterizes a transport time for the transport of the reactants to the flame front, where the combustion starts, a "heating time", which the
- reaction kinetic delay time Time for the heating up of the reactants to the temperature required for ignition, as well as a "reaction kinetic delay time", which is determined by the course of the combustion itself. As a rule, the convective delay time clearly outweighs the other two summands.
- Throttling points, resonators and / or mufflers are used, see the mentioned book by Putnam, pp. 156-175, or that the fuel is supplied by an active modulation with the aim of decoupling the energy release from acoustic vibrations in the combustion chamber.
- active instability control Such a measure is referred to as “active instability control”; for explanation see the article "The ⁇ active instability control 'as a method of investigation for self-excited combustion stabilities" by S. Gleis and D. Vortmeyer, VDI-Reports No. 765 (1989), p. 645 -656.
- DE 42 41 729 AI describes an actuator by means of which a mass flow or pressure fluctuation can be impressed.
- the actuator is proposed for use in the active control of combustion instabilities in liquid fuel burners and in devices for atomizing liquids.
- the conventional passive measures for suppressing combustion vibrations aim to stabilize the operation of the system by shifting the acoustic properties of subsystems so that combustion vibrations no longer occur over the entire desired operating range. These measures require resources which have to be adapted to the respective system in individual cases and which always involve the risk that known unstable operating points are stabilized, but new instabilities are caused under other operating conditions.
- DE 43 36 096 AI specifies a device for reducing vibrations in combustion chambers.
- a plurality of burners are arranged in the flow direction in front of the combustion chamber, with adjacent burners each being shifted from one another in the direction of flow by a predetermined distance.
- This predetermined distance is chosen so that when the burners are in operation, the temperature fluctuations of neighboring burners which propagate in the direction of flow are just opposite.
- combustion zones with a positive and a negative deviation from an average temperature are thus adjacent to one another, these regions being mixed in the direction of flow and thus a uniform temperature. This is intended to prevent a combustion oscillation induced by temperature fluctuations and therefore also pressure fluctuations due to different densities.
- the object of the invention to provide new passive measures on a combustion chamber with a plurality of burners, which are suitable for reliably suppressing combustion vibrations.
- the measures should be applicable to both liquid and gaseous fuels regardless of the apparatus and non-functional details of the combustion chamber. No moving parts or other active components should be used.
- the invention is intended to specify both a corresponding method and a corresponding device.
- a method for combusting fuel with air in a combustion chamber is specified, to which the air is supplied through at least one air inlet and the fuel is supplied through several burners, each burner having an associated delay time, which is one Corresponds to the period of time after which an acoustic pulse m of the combustion chamber causes a thermal pulse in the combustion of the fuel supplied via this burner, and the supply of the fuel via the burner and the supply of air via the air inlet are controlled in such a way that the delay times of the Burners are significantly different from one another.
- the invention is based on the knowledge that in a combustion chamber, as is usually used in a gas turbine and which generally has a plurality of burners of the same type, the combustion of the burners can work together to stimulate combustion vibrations to an increased extent.
- a combustion chamber as is usually used in a gas turbine and which generally has a plurality of burners of the same type
- the combustion of the burners can work together to stimulate combustion vibrations to an increased extent.
- this one burner also excites every other burner m of the combustion chamber to oscillate.
- This effect manifests itself, for example, in the fact that there are sharp transitions between operating states with or without combustion vibrations in a combustion chamber with a plurality of burners of the same type. Since combustion vibrations always originate from several burners, very high amplitudes are also observed with such combustion vibrations.
- the invention provides burners with different acoustic properties, i. H. above all different delay times. As a result, the burners cannot excite one another and, moreover, a steaming effect can always be exploited, starting from a stable burner.
- the method is preferably designed such that the associated flows of the burners are substantially different from one another. This ensures that the thermodynamic conditions characterizing the individual operation of the burners are certainly different from one another and the difference in the delay times of the burners from one another is ensured.
- a burner is assigned an associated air inlet, through which the air is supplied to the combustion chamber in an associated flow, characterized in that the burners are designed essentially identically to one another, and the associated flow is throttled at e- apart from an associated air inlet, so that all associated currents are significantly different from one another.
- every associated air intake throttled the associated flow; this can be desirable in order to give the stream certain desired properties, for example to homogenize it.
- a further additional embodiment of the method in the event that each burner is assigned an associated air inlet through which the air is fed into an associated flow m the combustion chamber, and the associated flows are geometrically similar to one another, is characterized in that the Burners are geometrically similar to one another, but are of different sizes.
- This configuration is also of interest with regard to a corresponding device, since this configuration at least allows a single shape to be provided for the burners and only to be scaled differently for the production of the different burners. The difference in the delay times remains guaranteed because the delay time of a burner is not determined solely by its geometry and is therefore not variable on the scale.
- All of the described embodiments of the method can be developed in such a way that the fuel is fed to each burner in such a way that a mixing ratio predetermined for all burners is maintained between a rate of the supplied fuel and a rate of the air supplied through the associated air inlet.
- This configuration is of particular interest because it allows each burner to be operated optimally with regard to the overall thermal output desired by the combustion with regard to an always undesirable production of nitrogen oxides.
- the design requires an appropriately balanced fuel supply.
- it can also be provided that the fuel is fed to each burner at a rate predetermined for all burners. This does mean that individual burners may not be operated optimally with regard to the production of nitrogen oxides, but this may be acceptable in view of the simple fuel supply.
- the method for use in connection with a combustion chamber which is resonant for an acoustic oscillation with a certain period the associated delay time of each burner between an integral multiple minus a quarter and the integral multiple plus a quarter of the period lies.
- the term "integer multiple” also includes zero. It goes without saying that the delay time cannot, by definition, assume negative values.
- the feature that the combustion chamber is resonant for a certain acoustic oscillation should not be interpreted as a limitation to this effect. that only the combustion chamber should determine this resonance; it is understood that the combustion chamber is usually part of a more or less complex overall acoustic system, the resonance with all essential parameters being defined by the overall acoustic system.
- premix combustion is of particular interest because it takes place at lower temperatures than the diffusion combustion that can be achieved with simpler means and therefore significantly less than the diffusion combustion for product tion of nitrogen oxides. It is important in this context that the invention also compensates for the thermodynamic-acoustic problems of premixed combustion mentioned at the beginning.
- the method of any configuration is particularly excellent for use on a gas turbine, in which the air is provided from a compressor and flue gas, which arises in the combustion chamber by burning the fuel in the air, is fed to a turbine.
- a device for the combustion of fuel with air comprising: a combustion chamber in which fuel is burned with air; at least one air inlet for supplying air to the combustion chamber; a plurality of burners for supplying fuel to the combustion chamber, each burner having an associated delay time which corresponds to a time period after which an acoustic pulse in the combustion chamber causes a thermal pulse when the fuel passed through this burner is burned; and a fuel supply for supplying the fuel to the burners; characterized in that the delay times of the burners are significantly different from one another.
- a preferred development of the device is characterized in that the burners are geometrically different from one another.
- the burners in the device are geometrically identical to one another, and the fuel supply is set up to supply the fuel to the burners at respective rates, which rates are substantially different from one another.
- Another alternative is characterized in that an associated air inlet is assigned to each burner, and a throttle is provided on each but one or on each burner for throttling a flow of air flowing through the associated air inlet.
- a throttle can be, for example, an orifice upstream of the burner.
- a further development of the device is particularly preferred in such a way that the combustion chamber is resonant for an acoustic oscillation with a certain period duration and that for each burner the associated delay time lies between an integer multiple minus a quarter and the integer multiple plus a quarter of the period duration .
- This embodiment corresponds to an already explained embodiment of the method according to the invention, and all statements made for this apply analogously to the configuration of the device.
- the device for use on a gas turbine is particularly preferred, the combustion chamber being arranged between a compressor and a turbine of the gas turbine.
- acoustic vibration is characterized by a more or less symmetrical arrangement of standing acoustic waves in the overall oscillating system.
- the wavelength the acoustic vibrations corresponded to a half of the middle circumference of the annular combustion chamber. To suppress such a vibration, it would be advantageous to avoid two-fold or four-fold symmetries when arranging the burners.
- the invention does not require that there be no two burners with identical properties in the combustion chamber; the purpose of the invention can certainly be served with a combustion chamber to which several burners of several types of burners are connected.
- acoustic vibrations with amplitudes of 100 mbar were observed on a gas turbine with two silo combustion chambers of conventional type, each of which had six identical burners for the combustion of heating oil, when operating under 80 l of the nominal load relevant for the design.
- These acoustic vibrations could be eliminated by exchanging two of the six burners for slightly modified burners in each silo combustion chamber.
- the modified burners were designed so that they received about 8 o less fuel at nominal load than the unchanged burners.
- the modified burners were used so that they each included an unchanged burner between them.
- the modified configuration of the burners allowed the gas turbine to be operated up to 100 ° of its nominal load, without acoustic vibrations occurring at a noticeable height.
- FIG. 1 shows a gas turbine and a device for the combustion of a fuel with air
- 2 shows a plan view of a combustion chamber with a plurality of burners
- 3 shows a schematic cross section through a combustion chamber with several burners.
- FIG. 1 shows a gas turbine with a compressor 1 and a turbine 2, which drives the compressor 1 via a shaft 3.
- Compressed air passes from the compressor 1 via an air line 4 to the combustion chamber 5 and enters the combustion chamber 5 through air inlets 6, each of which is assigned to a burner 7, each burner 7 being arranged on a rear wall 8 of the combustion chamber 5 on.
- the burners 7 are supplied with fuel from a tank 9 via a pump 10 and a fuel line 11 which branches in front of the burners 7. This fuel burns in the combustion chamber 5 with the air supplied via the air line 4.
- the combustion chamber 5 is a structure capable of acoustic vibrations and can, if necessary, be regarded as a component of an overall system capable of acoustic vibrations, which includes, for example, the combustion chamber 5, a flue gas line 13 leading from it to the turbine 2 and optionally the air line 4 and the fuel line 11 .
- Acoustic vibrations of the combustion chamber 5, which vibrates all or as part of such an overall system, can be excited and maintained by fluctuations in the combustion of the fuel; in such a case one speaks of combustion vibrations. Such combustion vibrations can become so severe that the combustion chamber 5 and other parts of the gas turbine can be damaged.
- the burners 7 are designed differently from one another. This means that not all burners 7 have the same relevant properties, and in particular that the delay times characterizing the respective combustion process are different from one another. In this way, in the configuration according to FIG. 1, it is in any case excluded that the burners 7 collectively excite a combustion oscillation.
- the burners 7 FIG. 1 are shown as so-called diffusion burners, since they inject the fuel directly into the combustion chamber 5. In this case, the fuel can only mix with the supplied air in the combustion chamber 5, which experience has shown to occur by diffusion. Diffusion burners have a simple structure and are relatively uncomplicated to operate, but they are inferior to the more complicated premix burners, which will be explained with reference to FIG. 2, with regard to the production of nitrogen oxides.
- FIG. 2 shows a plan view of the rear wall 8 of a combustion chamber 5, viewed in the direction that the air flows to the combustion chamber 5.
- Five burners 7 are inserted into the rear wall 8, all of which are essentially identical to one another.
- Each burner 7 has a number of swirl blades 14 which impart a swirl to the air which passes through it.
- Such a swirl is advantageous for the combustion itself and for the intimate mixing of the fuel with the air.
- the nozzles 12 Provided in the swirl vanes 14 are the nozzles 12 from which the fuel enters the air before it flows into the combustion chamber 5 and the fuel can ignite. Accordingly, the burners 7 shown in FIG. 2 are so-called “premix burners”.
- a premix burner brings a mixture from fuel and air with a defined composition for combustion, so that the combustion can be controlled much more sensitively than with a diffusion burner, where the process of mixing fuel and air is practically not controllable
- each burner 7 the blades 14 surround a hub 15; this hub 15 can serve to supply fuel to the nozzles 12.
- orifices 16 are mounted in front of four of the five burners 7, each of which partially covers the corresponding swirl blades 14 and thus acts as a throttle for the air flow entering the burner 7. This has the effect that the decisive operating parameters of all burners 7 are different from one another, so that the burner 7 cannot work together to excite combustion vibrations in the combustion chamber 5.
- the explanations made as preferred embodiments of the invention also apply to the exemplary embodiment according to FIG. 2.
- FIG. 3 shows a longitudinal section through a combustion chamber 5 along with its rear wall 8 and two burners 7.
- the burners 7 are again designed as premix burners.
- Each burner 7 shows three nozzles 12 for supplying fuel, all of which are arranged on the hub 15.
- the fuel reaches the swirl blades 14 from two of these nozzles, so that it is mixed with the air flowing through.
- a nozzle 12 directly faces the interior of the combustion chamber 5.
- This nozzle 12 forms a so-called “pilot flame” in which combustion takes place in the manner of a diffusion burner; this pilot flame serves to stabilize the combustion of the mixture of air and fuel that is generated between the swirl blades 14 and usually has a significant excess of oxygen. This allows the
- the production of heat by the burner 7 can be regulated within wide limits.
- the two premix burners are geometrically similar, i.e. H. that they are only in their size, but not in theirs
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP51415398A JP4249263B2 (ja) | 1996-09-16 | 1997-08-28 | 空気を用いた燃料燃焼方法及び装置 |
EP97941847A EP0925472B1 (de) | 1996-09-16 | 1997-08-28 | Verfahren zur unterdrückung von verbrennungsschwingungen und einrichtung zur verbrennung von brennstoff mit luft |
DE59703302T DE59703302D1 (de) | 1996-09-16 | 1997-08-28 | Verfahren zur unterdrückung von verbrennungsschwingungen und einrichtung zur verbrennung von brennstoff mit luft |
US09/272,748 US6052986A (en) | 1996-09-16 | 1999-03-16 | Method and device for burning fuel with air |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19637725.0 | 1996-09-16 | ||
DE19637725 | 1996-09-16 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/272,748 Continuation US6052986A (en) | 1996-09-16 | 1999-03-16 | Method and device for burning fuel with air |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1998012478A1 true WO1998012478A1 (de) | 1998-03-26 |
Family
ID=7805797
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE1997/001881 WO1998012478A1 (de) | 1996-09-16 | 1997-08-28 | Verfahren und einrichtung zur verbrennung von brennstoff mit luft |
Country Status (6)
Country | Link |
---|---|
US (1) | US6052986A (de) |
EP (1) | EP0925472B1 (de) |
JP (1) | JP4249263B2 (de) |
DE (1) | DE59703302D1 (de) |
RU (1) | RU2186298C2 (de) |
WO (1) | WO1998012478A1 (de) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2000009945A1 (en) * | 1998-08-11 | 2000-02-24 | Asea Brown Boveri Ab | Arrangement for reduction of acoustinc vibrations in a combustion chamber |
EP0952392A3 (de) * | 1998-04-15 | 2000-07-19 | Mitsubishi Heavy Industries, Ltd. | Brennkammer |
DE19939235A1 (de) * | 1999-08-18 | 2001-02-22 | Asea Brown Boveri | Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens |
DE10164099A1 (de) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoffeinspritzung |
EP1493972A1 (de) * | 2003-07-04 | 2005-01-05 | Siemens Aktiengesellschaft | Brennereinheit für eine Gasturbine und Gasturbine |
EP1906093A2 (de) * | 2006-09-26 | 2008-04-02 | United Technologies Corporation | Verfahren zur Steuerung thermoakustischer Instabilitäten in einer Brennkammer |
EP2119964A1 (de) * | 2008-05-15 | 2009-11-18 | ALSTOM Technology Ltd | Emissionsreduktionsverfahren für eine Brennkammer |
US7827777B2 (en) | 2008-05-15 | 2010-11-09 | Alstom Technology Ltd. | Combustor with reduced carbon monoxide emissions |
EP2848865A1 (de) * | 2013-09-12 | 2015-03-18 | Alstom Technology Ltd | Thermoakustisches Stabilisierungsverfahren |
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DE19948674B4 (de) * | 1999-10-08 | 2012-04-12 | Alstom | Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen |
GB0019533D0 (en) * | 2000-08-10 | 2000-09-27 | Rolls Royce Plc | A combustion chamber |
US6931853B2 (en) * | 2002-11-19 | 2005-08-23 | Siemens Westinghouse Power Corporation | Gas turbine combustor having staged burners with dissimilar mixing passage geometries |
US20070074518A1 (en) * | 2005-09-30 | 2007-04-05 | Solar Turbines Incorporated | Turbine engine having acoustically tuned fuel nozzle |
US7703288B2 (en) * | 2005-09-30 | 2010-04-27 | Solar Turbines Inc. | Fuel nozzle having swirler-integrated radial fuel jet |
US20070089427A1 (en) * | 2005-10-24 | 2007-04-26 | Thomas Scarinci | Two-branch mixing passage and method to control combustor pulsations |
US8028512B2 (en) | 2007-11-28 | 2011-10-04 | Solar Turbines Inc. | Active combustion control for a turbine engine |
US20110048022A1 (en) * | 2009-08-29 | 2011-03-03 | General Electric Company | System and method for combustion dynamics control of gas turbine |
EP2423589A1 (de) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Brenneranordnung |
EP2796789B1 (de) * | 2013-04-26 | 2017-03-01 | General Electric Technology GmbH | Rohrbrennkammer für eine Rohr-Ring Anordnung in einer Gasturbine |
RU2739877C1 (ru) * | 2020-07-22 | 2020-12-29 | Гришин Кирилл Вячеславович | Блок горелок печи для огневых испытаний |
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- 1997-08-28 EP EP97941847A patent/EP0925472B1/de not_active Expired - Lifetime
- 1997-08-28 RU RU99107571/06A patent/RU2186298C2/ru active
- 1997-08-28 DE DE59703302T patent/DE59703302D1/de not_active Expired - Lifetime
- 1997-08-28 JP JP51415398A patent/JP4249263B2/ja not_active Expired - Lifetime
- 1997-08-28 WO PCT/DE1997/001881 patent/WO1998012478A1/de active IP Right Grant
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1999
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US6267583B1 (en) | 1998-04-15 | 2001-07-31 | Mistubishi Heavy Industries, Ltd. | Combustor |
JP2002522741A (ja) * | 1998-08-11 | 2002-07-23 | エービービー アクチボラゲット | 燃焼室の音響振動を低減する構成 |
US6430930B1 (en) | 1998-08-11 | 2002-08-13 | Abb Ab | Arrangement for reduction of acoustic vibrations in a combustion chamber |
WO2000009945A1 (en) * | 1998-08-11 | 2000-02-24 | Asea Brown Boveri Ab | Arrangement for reduction of acoustinc vibrations in a combustion chamber |
DE19939235A1 (de) * | 1999-08-18 | 2001-02-22 | Asea Brown Boveri | Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens |
US6449951B1 (en) | 1999-08-18 | 2002-09-17 | Alstom | Combustion device for generating hot gases |
US6581385B2 (en) | 1999-08-18 | 2003-06-24 | Alstom | Combustion device for generating hot gases |
DE19939235B4 (de) * | 1999-08-18 | 2012-03-29 | Alstom | Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens |
US7241138B2 (en) | 2001-12-24 | 2007-07-10 | Alstom Technology Ltd. | Burner with stepped fuel injection |
DE10164099A1 (de) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoffeinspritzung |
WO2005003634A1 (de) * | 2003-07-04 | 2005-01-13 | Siemens Aktiengesellschaft | Brennereinheit für eine gasturbine und gasturbine |
EP1493972A1 (de) * | 2003-07-04 | 2005-01-05 | Siemens Aktiengesellschaft | Brennereinheit für eine Gasturbine und Gasturbine |
EP1906093A2 (de) * | 2006-09-26 | 2008-04-02 | United Technologies Corporation | Verfahren zur Steuerung thermoakustischer Instabilitäten in einer Brennkammer |
EP1906093A3 (de) * | 2006-09-26 | 2011-06-29 | United Technologies Corporation | Verfahren zur Steuerung thermoakustischer Instabilitäten in einer Brennkammer |
US8037688B2 (en) | 2006-09-26 | 2011-10-18 | United Technologies Corporation | Method for control of thermoacoustic instabilities in a combustor |
EP2119964A1 (de) * | 2008-05-15 | 2009-11-18 | ALSTOM Technology Ltd | Emissionsreduktionsverfahren für eine Brennkammer |
US7726019B2 (en) | 2008-05-15 | 2010-06-01 | Alstom Technology Ltd. | Method for reducing emissions from a combustor |
US7827777B2 (en) | 2008-05-15 | 2010-11-09 | Alstom Technology Ltd. | Combustor with reduced carbon monoxide emissions |
EP2848865A1 (de) * | 2013-09-12 | 2015-03-18 | Alstom Technology Ltd | Thermoakustisches Stabilisierungsverfahren |
Also Published As
Publication number | Publication date |
---|---|
JP2001503843A (ja) | 2001-03-21 |
EP0925472A1 (de) | 1999-06-30 |
EP0925472B1 (de) | 2001-04-04 |
US6052986A (en) | 2000-04-25 |
RU2186298C2 (ru) | 2002-07-27 |
DE59703302D1 (de) | 2001-05-10 |
JP4249263B2 (ja) | 2009-04-02 |
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