EP0925472B1 - Verfahren zur unterdrückung von verbrennungsschwingungen und einrichtung zur verbrennung von brennstoff mit luft - Google Patents
Verfahren zur unterdrückung von verbrennungsschwingungen und einrichtung zur verbrennung von brennstoff mit luft Download PDFInfo
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- EP0925472B1 EP0925472B1 EP97941847A EP97941847A EP0925472B1 EP 0925472 B1 EP0925472 B1 EP 0925472B1 EP 97941847 A EP97941847 A EP 97941847A EP 97941847 A EP97941847 A EP 97941847A EP 0925472 B1 EP0925472 B1 EP 0925472B1
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- European Patent Office
- Prior art keywords
- burner
- fuel
- air
- burners
- combustion chamber
- 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
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 150
- 239000000446 fuel Substances 0.000 title claims abstract description 61
- 238000000034 method Methods 0.000 title claims abstract description 31
- 230000010355 oscillation Effects 0.000 title claims description 8
- 230000001629 suppression Effects 0.000 title 1
- 239000007789 gas Substances 0.000 claims description 13
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 5
- 239000003546 flue gas Substances 0.000 claims description 5
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 21
- 238000009792 diffusion process Methods 0.000 description 11
- 238000004519 manufacturing process Methods 0.000 description 10
- 230000003993 interaction Effects 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
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- 238000013461 design Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000011835 investigation Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 239000000376 reactant Substances 0.000 description 2
- 230000007306 turnover Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 206010053615 Thermal burn Diseases 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
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- 230000001419 dependent effect Effects 0.000 description 1
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- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000012549 training Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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 suppressing combustion vibrations during a combustion of Fuel with air in a combustion chamber, which by at least an air intake through the air and through several burners the fuel are supplied, each burner having an associated one Delay time, which corresponds to a period of time, after which an acoustic pulse in the combustion chamber thermal impulse in the combustion of this burner fuel supplied.
- the invention relates also a corresponding device for combustion of fuel with air.
- the invention relates in particular to a method and a device of the type mentioned for use in a gas turbine, a gas turbine being a composite of a Compressor for air, comprising a combustion device at least one combustion chamber for burning a fuel in the air with the formation of a flue gas and a turbine in the true sense to relax the flue gas is.
- the turbine can be made up of several parts, i.e. several series connected Partial turbines include; the same applies to the compressor.
- the compressor is in particular a turbo compressor.
- the turbine drives as part of common practice the compressor.
- the invention relates to the task of damping or avoiding acoustic vibrations in a combustion chamber, which Vibrations induced by the combustion and as "Burning vibrations" are known.
- thermodynamic operating parameters such as air ratio and thermal power
- unstable operating conditions are due to correlated fluctuations in heat production with the combustion and the static pressure in the combustion chamber and / or in this upstream and downstream parts of the system. These fluctuations are expressed in that in the Combustion chamber self-excited acoustic vibrations occur. These acoustic vibrations cause an increased one Noise pollution in the vicinity of the affected plant increased mechanical and thermal stresses on the combustion chamber and other parts of the system which are quite short Time can lead to complete or partial failure.
- a combustion vibration is generally based on one Interaction between the flow of the used Burner escaping reactants and energy turnover when burning, the interaction being related with one in the combustion chamber and connected system parts occurring acoustic resonance a stable acoustic Vibration generates and maintains.
- the training and maintenance of acoustic The energy required for vibration comes from the combustion process delivered itself.
- Derivable from the Rayleigh criterion is also a criterion which is the period of an acoustic vibration, for which discusses the possibility of their occurrence in a relationship relies on a burner and its operation essential characterizing "delay time".
- This delay time is a time period after which an acoustic pulse in the Combustion chamber to which the burner is connected, one thermal impulse during the combustion of the burner fuel supplied. Relating to one in the Combustion chamber stable vibration and one of these thermal vibration caused by the burner, ie a periodic fluctuation in energy turnover at combustion caused by the burner corresponds to the delay time a phase difference between the acoustic and thermal vibration. It is important to point this out to Büchner's thesis, pp.
- the delay time of a burner in a combustion chamber sets composed of different summands, each based on individual components of the system from burner, combustion chamber and Flame are traceable.
- the on the burner and the combustion chamber Available summands are mainly determined due to the geometry of the burner and combustion chamber; one on the Flame itself is a summand that is essentially recyclable determines the properties of the combustion itself.
- the summand itself can be further broken down into a "convective Delay Time ", which is a transportation time for the transportation of the Reaction partner to the flame front, where the combustion begins, characterized a "heating time” which the Time for the reactants to heat up for ignition indicates the required temperature, and a “reaction kinetic delay time", which is due to the expiry the combustion itself is determined.
- the convective delay time clearly shows the other two summands.
- the conventional passive measures to suppress Combustion vibrations aim to operate the System by shifting the acoustic properties of Stabilize subsystems so that the entire desired Operating area no more combustion vibrations occur. These measures require funds in individual cases have to be adapted to the respective system and continuously involve the risk that known unstable operating points stabilized, however new instabilities under other operating conditions.
- DE 43 36 096 A1 describes a device for reducing Vibrations in combustion chambers specified.
- several burners arranged in front of the combustion chamber, with adjacent burners each in the direction of flow predetermined distance from each other are. This predetermined distance is chosen so that when the burner is in operation in the direction of flow spreading temperature fluctuations of neighboring burners straight are opposite.
- This predetermined distance is chosen so that when the burner is in operation in the direction of flow spreading temperature fluctuations of neighboring burners straight are opposite.
- This is said to be a combustion vibration induced by temperature fluctuations and thus prevent pressure fluctuations due to different densities.
- the object of the invention to create new passive ones Specify measures on a combustion chamber with several burners, which reliably suppresses combustion vibrations are suitable.
- the measures should both independent for liquid as well as for gaseous fuels of apparatus and functional details of the Combustion chamber applicable. There should be no moving parts or other active components are used.
- the invention should be both a corresponding procedure as well specify an appropriate facility.
- the invention is based on the knowledge that it is in a Combustion chamber, as is usually used in a gas turbine is and usually several similar burners has, by interaction of the burner to a reinforced Excitation of combustion vibrations can come.
- Form thermal vibrations occur with only one burner in interaction with acoustic vibrations in the combustion chamber off, this one burner excites every other burner also starts to vibrate in the combustion chamber.
- This effect is expressed, for example, in the fact that it is in a combustion chamber with several, similar burners each with sharp transitions between operating states with or without combustion vibrations gives. Since combustion vibrations occur always start from several burners, such combustion vibrations very high amplitudes were also observed.
- the invention provides burners with different acoustic properties, d. H. especially different Delay times to be provided. This allows the Do not excite burners among themselves and it can also Always a damping effect based on a stable working burner.
- the method is used in a case where everyone Burner is assigned an associated air inlet through which associated air inlet the air in an associated Current is supplied to the combustion chamber, designed so that the associated currents of the burners differ considerably from one another are. This ensures that the respective Operation of the burner characterizing thermodynamic Relationships are certainly different from each other and the difference in the delay times between the burners is guaranteed.
- each Burner is assigned an associated air inlet through which the air is supplied to the combustion chamber in an associated stream is characterized in that the burner in are designed essentially the same among each other, and on each apart from an associated air inlet, the associated stream is throttled so that all associated currents are essential are different from each other.
- the associated flow throttled may be associated with each Air inlet the associated flow throttled; this may be desirable to give the stream certain desirable properties to give, e.g. to homogenize him.
- each burner is assigned an associated air inlet is through which the air flows into an associated stream Combustion chamber is guided, and the associated streams are geometrically similar to each other, is characterized by that the burners are geometrically similar to one another, however are different sizes.
- This configuration is also in With regard to an appropriate facility of interest, since this configuration at least allows one for the burners to provide only shape and this for the production of the different Simply scale the burner differently. The difference in the delay times remains guaranteed because the delay time of a burner is not by itself determines its geometry and is therefore not scale-invariant.
- each burner's fuel is supplied in such a way that a mixing ratio specified for all burners between a rate of fuel supplied and a rate of through the associated air intake supplied air is observed.
- This configuration is of particular interest because it allows everyone Burner in terms of total combustion desired thermal performance optimal with regard to a always operate undesirable production of nitrogen oxides.
- the design requires an appropriately upgraded one Fuel supply.
- each burner Fuel is supplied at a rate specified for all burners becomes. While this means that individual burners are under Maybe not optimal with regard to the production of Nitrogen oxides are operated, but what with regard to simple fuel supply may be acceptable.
- the method for use in is of particular importance Relation to a combustion chamber that is resonant for one acoustic vibration with a certain period, whereby the associated delay time of each burner between one integer multiples minus a quarter and the integer Multiples plus a quarter of the period. This corresponds to the adherence to that of Herrmann et al as well Büchner criterion derived from the Rayleigh criterion between the delay time and the period in question taken acoustic vibration.
- the term "Integer multiple" also includes zero. It it goes without saying that the delay time is by definition not negative Can assume values.
- combustion chamber should be resonant for a certain acoustic vibration should not be construed as a limitation that for this resonance can only determine the combustion chamber alone may; it goes without saying that the combustion chamber as a rule Part of a more or less complex overall acoustic system is, the resonance with all essential parameters is defined by the overall acoustic system.
- An embodiment of the process is also of particular interest in that the fuel with in each burner the air is mixed before being burned in the combustion chamber becomes.
- the Premix combustion is of particular interest, because they are at lower temperatures than those with simpler ones Diffusion combustion to be effected expires and therefore significantly less than diffusion combustion for production of nitrogen oxides.
- the invention also compensates for the thermodynamic-acoustic problems mentioned at the beginning premix combustion.
- the process of any configuration is particularly excellent for use on a gas turbine, the air is provided from a compressor and flue gas, which in the combustion chamber is created by the fuel in the Air is burned and fed to a turbine.
- a preferred further development of the facility is emerging characterized in that the burners differ geometrically from one another are.
- the burners in the device are geometric right next to each other, and the fuel supply is set up to supply the fuel to the burners with respective Guess which rates are significantly different from each other are.
- Another alternative is characterized in that everyone Burner is assigned an associated air inlet, and on a throttle for everyone except one, or on each burner Throttling a flowing through the associated air inlet Current of the air is provided.
- a choke can for example, an aperture upstream of the burner.
- a further development of the device is particularly preferred in that the combustion chamber is resonant for an acoustic Vibration with a certain period, and that the associated delay time between one for each burner integer multiples minus a quarter and the integer Multiples plus a quarter of the period lies.
- the device is particularly preferred for use on a Gas turbine, the combustion chamber between a compressor and a turbine of the gas turbine is arranged.
- an asymmetrical arrangement if possible the burner is preferred. Like the asymmetrical arrangement can look in individual cases, and according to which criterion a "Sufficient asymmetry" can be determined, remains for everyone In individual cases, at the discretion of those who are relevant and active Leave person.
- the main one to be observed Principle boils down to an acoustic vibration is usually characterized by a more or less symmetrical arrangement of standing acoustic waves in the vibrating overall system.
- a combustion oscillation observed on an annular combustion chamber which was characterized by acoustic Waves that closed around the annular combustion chamber.
- the wavelength of the acoustic vibrations corresponded to this half an average circumference of the annular combustion chamber. To suppress such a vibration, it would be advantageous in the arrangement of the burners two-fold or four-fold To avoid symmetries.
- the invention does not require that there be none in the combustion chamber may give two burners with identical properties; the Purpose of the invention can be served with a Combustion chamber to which of several types of burners each several burners are connected.
- a gas turbine with two silo combustion chambers conventional type, each of which is the same as six Burner for the combustion of heating oil exhibited when operating under 80% of the nominal load relevant for the design acoustic Vibrations with amplitudes of 100 mbar observed.
- These acoustic vibrations could be eliminated by against each of the six burners in each silo combustion chamber slightly modified burners were replaced.
- the modified Burners were designed so that they operate at nominal load Received 8% less fuel 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 operate the gas turbine up to 100% of its nominal load, without acoustic vibrations occurring at a noticeable height.
- FIG. 1 shows a gas turbine with a compressor 1 and one Turbine 2, which drives the compressor 1 via a shaft 3.
- Compressed air passes from the compressor 1 an air line 4 to the combustion chamber 5 and enters it through air inlets 6, each of which is assigned to a burner 7 is, each burner 7 in a rear wall 8 of the combustion chamber 5 is arranged in the combustion chamber 5.
- the burners 7 are from a tank 9 via a pump 10 and a fuel line 11, which branches in front of the burners 7, fueled. This fuel burns in the Combustion chamber 5 with the one supplied via the air line 4 Air.
- the combustion chamber 5 is capable of acoustic vibrations Form and can, if necessary as part of a overall system capable of acoustic vibrations, which, for example combustion chamber 5, one of them to turbine 2 leading flue gas line 13 and possibly the air line 4 and the fuel line 11 are considered.
- Acoustic vibrations in the combustion chamber 5, which alone or vibrates as part of such an overall system, can be caused by fluctuations in the combustion of the fuel be stimulated and maintained; in such a Fall one speaks of combustion vibrations.
- Such combustion vibrations can become so strong that the combustion chamber 5 and other parts of the gas turbine may be damaged can.
- Burner 7 designed differently from one another. This leads to to the fact that not all burners 7 have the same relevant properties have, and in particular that the respective Delay times characterizing the combustion process differ are from each other. That way it is with the Configuration according to FIG 1 in any case excluded that the Burner 7 collectively stimulate combustion oscillation.
- the burners 7 in FIG. 1 are shown as so-called diffusion burners, since they put the fuel directly into the combustion chamber 5 inject.
- the fuel can only in the combustion chamber 5 mix with the supplied air what experience has shown that diffusion takes place.
- Diffusion burner are simple and can be operated relatively easily, but they are the most concerned with the production of nitrogen oxides complicated premix burners, which are still based on FIG be explained, inferior.
- FIG. 2 shows a plan view of the rear wall 8 of a combustion chamber 5, seen in the direction in which the air flows to the combustion chamber 5.
- five burners 7, all of which are essentially identical to one another are designed.
- Each burner 7 has a number of Swirl blades 14, which one of the air that passes through it Imprint swirl. Such a twist is beneficial for that Combustion itself and for the intimate mixing of the fuel with the air.
- the swirl blades 14 Provided in the swirl blades 14 are the nozzles 12 from which the fuel gets into the air, before it flows into the combustion chamber 5 and the Fuel can ignite. Accordingly, those in FIG. 2 illustrated burner 7 so-called "premix burner".
- a premix burner brings a mixture of fuel and air with defined Composition for combustion, so that a much more sensitive Control of the combustion than with a diffusion burner, where the process of mixing fuel and air is practically not controllable, is possible. It also runs Combustion in a premix burner at significantly less Maximum temperatures than with a diffusion burner, which is advantageous for avoiding the production of nitrogen oxides is.
- the blades 14 surround a hub 15; this hub 15 can serve to supply fuel to the nozzles 12 to lead.
- FIG. 3 shows a longitudinal section through a combustion chamber 5 together with their rear wall 8 and two burners 7.
- the burners 7 are again designed as a premix burner.
- Each burner 7 shows three nozzles 12 for supplying fuel, all of which the hub 15 are arranged. Arrived from two of these nozzles the fuel between the swirl blades 14 so that it with the air flowing through it is mixed.
- a nozzle 12 is immediate facing the interior of the combustion chamber 5.
- This nozzle 12 forms a so-called "pilot flame” in which one Combustion takes place in the manner of a diffusion burner; this pilot flame is used to burn the between generated the swirl blades 14 and usually a clear one Excess of oxygen-containing mixture Stabilize air and fuel. This allows the Production of heat by the burner 7 within wide limits regulate.
- the two premix burners are geometrically similar to each other, d. H. that they are only in their size, but not in theirs Differentiate proportions. This also results in a difference the relevant operating parameters, which for Exclusion of interaction of these burners 7 in the excitation a combustion vibration in the combustion chamber 5 is used becomes.
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
Description
- FIG 1
- eine Gasturbine und eine Einrichtung zur Verbrennung
- eines Brennstoffes mit Luft;
- FIG 2
- eine Draufsicht auf eine Brennkammer mit mehreren Brennern;
- FIG 3
- einen schematisierten Querschnitt durch eine Brennkammer mit mehreren Brennern.
Claims (17)
- Verfahren zur Unterdrückung von Verbrennungsschwingungen bei einer Verbrennung von Brennstoff mit Luft in einer Brennkammer (5), welcher durch zumindest einen Lufteinlaß (6) die Luft und durch mehrere Brenner (7) der Brennstoff zugeführt werden, wobei jeder Brenner (7) eine zugehörige Verzugszeit hat, welche einer Zeitdauer entspricht, nach welcher ein akustischer Impuls in der Brennkammer (5) einen thermischen Impuls bei der Verbrennung des über diesen Brenner (7) zugeführten Brennstoffs hervorruft, dadurch gekennzeichnet, daß die Zuführung des Brennstoffs über die Brenner (7) und die Zuführung der Luft über den Lufteinlaß (6) derart eingestellt werden, daß die Verzugszeiten der Brenner (7) wesentlich verschieden untereinander sind.
- Verfahren nach Anspruch 1, bei dema) die Brenner (7) ein zugehöriger Lufteinlaß (6) zugeordnet ist, durch welchen die Luft in einem zugehörigen Strom der Brennkammer (5) zugeführt wird; undb) die zugehörigen Ströme der Brenner (7) wesentlich verschieden untereinander sind.
- Verfahren nach Anspruch 1, bei dema) die Brenner (7) im wesentlichen gleich untereinander gestaltet sind;b) jedem Brenner (7) ein zugehöriger Lufteinlaß (6) zugeordnet ist, durch welchen die Luft in einem zugehörigen Strom der Brennkammer (5) zugeführt wird; undc) an jedem außer einem zugehörigen Lufteinlaß (6) der zugehörige Strom gedrosselt wird, so daß alle zugehörigen Ströme wesentlich verschieden untereinander sind.
- Verfahren nach Anspruch 1, bei dema) die Brenner (7) im wesentlichen gleich untereinander gestaltet sind;b) jedem Brenner (7) ein zugehöriger Lufteinlaß (6) zugeordnet ist, durch welchen die Luft in einem zugehörigen Strom der Brennkammer (5) zugeführt wird; undc) an jedem zugehörigen Lufteinlaß (6) der zugehörige Strom gedrosselt wird, wobei die zugehörigen Ströme verschieden untereinander sind.
- Verfahren nach Anspruch 1, bei dema) die Brenner (7) untereinander geometrisch ähnlich, jedoch verschieden groß sind;b) jedem Brenner (7) ein zugehöriger Lufteinlaß (6) zugeordnet ist, durch welchen die Luft in einem zugehörigen Strom in die Brennkammer (5) geführt wird, wobei die zugehörigen Ströme untereinander geometrisch ähnlich sind.
- Verfahren nach einem der Ansprüche 1 bis 5, bei dem jedem Brenner (7) der Brennstoff derart zugeführt wird, daß ein für alle Brenner (7) vorgegebenes Mischungsverhältnis zwischen einer Rate des zugeführten Brennstoffs und einer stöchiometrischen Rate entsprechend der durch den zugehörigen Lufteinlaß (6) zugeführten Luft eingehalten wird.
- Verfahren nach einem der Ansprüche 1 bis 5, bei dem jedem Brenner (7) der Brennstoff mit einer für alle Brenner (7) vorgegebenen Rate zugeführt wird.
- Verfahren nach einem der vorhergehenden Ansprüche, bei dem die Brennkammer (5) resonant ist für eine akustische Schwingung mit einer bestimmten Periodendauer, und bei dem für jeden Brenner (7) die zugehörige Verzugszeit zwischen einem ganzzahligen Vielfachen minus einem Viertel und dem ganzzahligen Vielfachen plus einem Viertel der Periodendauer liegt.
- Verfahren nach einem der vorhergehenden Ansprüche, bei dem in jedem Brenner (7) der Brennstoff mit der Luft vermischt wird, bevor er in der Brennkammer (5) verbrannt wird.
- Verfahren nach einem der vorhergehenden Ansprüche, bei dem die Luft aus einem Verdichter (1) bereitgestellt wird, und bei dem Rauchgas, welches in der Brennkammer (5) entsteht, indem der Brennstoff in der Luft verbrannt wird, einer Turbine (2) zugeführt wird.
- Einrichtung zur Verbrennung von Brennstoff mit Luft, umfassenddadurch gekennzeichnet, daß die Verzugszeiten der Brenner (7) wesentlich verschieden untereinander sind.a) eine Brennkammer (5), in der der Brennstoff mit der Luft verbrannt wird;b) zumindest einen Lufteinlaß (6) zur Zuführung der Luft in die Brennkammer (5);c) mehrere Brenner (7) zur Zuführung des Brennstoffes in die Brennkammer (5), wobei jeder Brenner (7) eine zugehörige Verzugszeit hat, welche einer Zeitdauer entspricht, nach welcher ein akustischer Impuls in der Brennkammer (5) einen thermischen Impuls bei der Verbrennung des über diesen Brenner (7) zugeführten Brennstoffs hervorruft; undd) eine Brennstoffzufuhr (9, 10, 11) zur Zufuhr des Brennstoffs zu den Brennern (7);
- Einrichtung nach Anspruch 11, bei der die Brenner (7) geometrisch verschieden untereinander sind.
- Einrichtung nach Anspruch 11, bei der die Brenner (7) geometrisch gleich untereinander sind, und bei der die Brennstoffzufuhr (9, 10, 11) eingerichtet ist zur Zuführung des Brennstoffs zu den Brennern (7) mit jeweiligen Raten, welche wesentlich verschieden untereinander sind.
- Einrichtung nach einem der Ansprüche 11 bis 13, bei der jedem Brenner (7) ein zugehöriger Lufteinlaß (6) zugeordnet ist und an jedem außer einem Brenner (7) eine Drossel (16) zur Drosselung eines den zugehörigen Lufteinlaß (6) durchströmenden Stromes der Luft vorgesehen ist.
- Einrichtung nach einem der Ansprüche 11 bis 13, bei der jedem Brenner (7) ein zugehöriger Lufteinlaß (6) zugeordnet ist und an jedem Brenner (7) eine Drossel (16) zur Drosselung einer den zugehörigen Lufteinlaß (6) durchströmenden Stromes der Luft vorgesehen ist.
- Einrichtung nach einem der Ansprüche 11 bis 15, bei der die Brennkammer (5) resonant ist für eine akustische Schwingung mit einer bestimmten Periodendauer, und bei der für jeden Brenner (7) die zugehörige Verzugszeit zwischen einem ganzzahligen Vielfachen minus einem Viertel und dem ganzzahligen Vielfachen plus einem Viertel der Periodendauer liegt.
- Einrichtung nach einem der Ansprüche 11 bis 16, bei der die Brennkammer (5) in einer Gasturbine (1, 2, 3, 4, 5, 13) zwischen einem Verdichter (1) und einer Turbine (2) angeordnet ist.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19637725 | 1996-09-16 | ||
| DE19637725 | 1996-09-16 | ||
| PCT/DE1997/001881 WO1998012478A1 (de) | 1996-09-16 | 1997-08-28 | Verfahren und einrichtung zur verbrennung von brennstoff mit luft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0925472A1 EP0925472A1 (de) | 1999-06-30 |
| EP0925472B1 true EP0925472B1 (de) | 2001-04-04 |
Family
ID=7805797
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97941847A Expired - Lifetime EP0925472B1 (de) | 1996-09-16 | 1997-08-28 | Verfahren zur unterdrückung von verbrennungsschwingungen 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 (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19948674B4 (de) * | 1999-10-08 | 2012-04-12 | Alstom | Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen |
Families Citing this family (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69910106T2 (de) | 1998-04-15 | 2004-06-17 | Mitsubishi Heavy Industries, Ltd. | Brennkammer |
| SE9802707L (sv) * | 1998-08-11 | 2000-02-12 | Abb Ab | Brännkammaranordning och förfarande för att reducera inverkan av akustiska trycksvängningar i en brännkammaranordning |
| DE19939235B4 (de) | 1999-08-18 | 2012-03-29 | Alstom | Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens |
| GB0019533D0 (en) | 2000-08-10 | 2000-09-27 | Rolls Royce Plc | A combustion chamber |
| DE10164099A1 (de) | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoffeinspritzung |
| US6931853B2 (en) * | 2002-11-19 | 2005-08-23 | Siemens Westinghouse Power Corporation | Gas turbine combustor having staged burners with dissimilar mixing passage geometries |
| EP1493972A1 (de) * | 2003-07-04 | 2005-01-05 | Siemens Aktiengesellschaft | Brennereinheit für eine Gasturbine und Gasturbine |
| 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 |
| US8037688B2 (en) | 2006-09-26 | 2011-10-18 | United Technologies Corporation | Method for control of thermoacoustic instabilities in a combustor |
| US8028512B2 (en) | 2007-11-28 | 2011-10-04 | Solar Turbines Inc. | Active combustion control for a turbine engine |
| EP2119966A1 (de) | 2008-05-15 | 2009-11-18 | ALSTOM Technology Ltd | Brennkammer mit reduzierten Kohlenstoffmonoxidemissionen |
| EP2119964B1 (de) * | 2008-05-15 | 2018-10-31 | Ansaldo Energia IP UK Limited | Emissionsreduktionsverfahren für eine Brennkammer |
| 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 |
| EP2848865A1 (de) * | 2013-09-12 | 2015-03-18 | Alstom Technology Ltd | Thermoakustisches Stabilisierungsverfahren |
| RU2739877C1 (ru) * | 2020-07-22 | 2020-12-29 | Гришин Кирилл Вячеславович | Блок горелок печи для огневых испытаний |
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| GB2275738B (en) * | 1987-01-24 | 1995-01-25 | Topexpress Ltd | Reducing reheat buzz in a gas turbine aeroengine |
| GB2239961A (en) * | 1990-01-02 | 1991-07-17 | Gen Electric | Control of combustion-induced instabilities |
| JPH0579629A (ja) * | 1991-09-19 | 1993-03-30 | Hitachi Ltd | 燃焼器およびその運転方法 |
| CZ114994A3 (en) | 1991-11-15 | 1994-08-17 | Siemens Ag | Device for suppressing vibrations induced by combustion within a combustion chamber |
| DE4202588C1 (en) * | 1992-01-30 | 1993-07-15 | Buderus Heiztechnik Gmbh, 6330 Wetzlar, De | Multi-bar atmospheric gas burner - has adjacent bars with different outlets giving different combustion characteristics |
| DE4336096B4 (de) | 1992-11-13 | 2004-07-08 | Alstom | Vorrichtung zur Reduktion von Schwingungen in Brennkammern |
| DE4241729A1 (de) | 1992-12-10 | 1994-06-16 | Stephan Dipl Ing Gleis | Aktuator zum Aufprägen von Massenstrom- bzw. Druckschwankungen auf unter Druck stehende Flüssigkeitsströme |
| DE4339094A1 (de) * | 1993-11-16 | 1995-05-18 | Abb Management Ag | Verfahren zur Dämpfung von thermoakustischen Schwingungen sowie Vorrichtung zur Durchführung des Verfahrens |
| DE4411623A1 (de) * | 1994-04-02 | 1995-10-05 | Abb Management Ag | Vormischbrenner |
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| US5644918A (en) * | 1994-11-14 | 1997-07-08 | General Electric Company | Dynamics free low emissions gas turbine combustor |
| US5809769A (en) * | 1996-11-06 | 1998-09-22 | The United States Of America As Represented By The United States Department Of Energy | Combustor oscillation attenuation via the control of fuel-supply line dynamics |
-
1997
- 1997-08-28 WO PCT/DE1997/001881 patent/WO1998012478A1/de not_active Ceased
- 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 RU RU99107571/06A patent/RU2186298C2/ru active
- 1997-08-28 EP EP97941847A patent/EP0925472B1/de not_active Expired - Lifetime
-
1999
- 1999-03-16 US US09/272,748 patent/US6052986A/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19948674B4 (de) * | 1999-10-08 | 2012-04-12 | Alstom | Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen |
Also Published As
| Publication number | Publication date |
|---|---|
| US6052986A (en) | 2000-04-25 |
| EP0925472A1 (de) | 1999-06-30 |
| JP4249263B2 (ja) | 2009-04-02 |
| DE59703302D1 (de) | 2001-05-10 |
| RU2186298C2 (ru) | 2002-07-27 |
| JP2001503843A (ja) | 2001-03-21 |
| WO1998012478A1 (de) | 1998-03-26 |
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