EP1963748A1 - Brennkammer mit brenner und zugehöriges betriebsverfahren - Google Patents
Brennkammer mit brenner und zugehöriges betriebsverfahrenInfo
- Publication number
- EP1963748A1 EP1963748A1 EP06830438A EP06830438A EP1963748A1 EP 1963748 A1 EP1963748 A1 EP 1963748A1 EP 06830438 A EP06830438 A EP 06830438A EP 06830438 A EP06830438 A EP 06830438A EP 1963748 A1 EP1963748 A1 EP 1963748A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- combustion chamber
- synthesis gas
- pilot
- pilot burner
- 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.)
- Granted
Links
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
- F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
Definitions
- the present invention relates to a method for operating a combustion chamber of a gas turbine, in particular a power plant.
- the invention also relates to a burner equipped with a catalytic pilot burner for a combustion chamber of a gas turbine. Furthermore, the invention relates to an annular combustion chamber, which is equipped with a plurality of such burners.
- a catalytic burner which can generate a hydrogen gas containing synthesis gas in operation from a rich fuel / air mixture and which can be used as a pilot burner for a normally lean burn burner of a combustion chamber of a gas turbine.
- Synthesis gas into the burner or in a combustion chamber of the combustion chamber the homogeneous combustion reaction that takes place in the combustion chamber during operation of the combustion chamber can be stabilized. In particular, this can be used to lower the extinguishing temperature of the combustion reaction in lean burners. Altogether thereby the combustion temperatures in the Combustion chamber of the combustion chamber can be reduced. This is of particular advantage because the formation of nitrogen oxides increases exponentially with the reaction temperature. However, in order to operate the combustion chamber with a higher power, the combustion chamber must be operated so that it reaches a higher outlet temperature.
- the inventive method is based on the general idea of controlling the pilot burner as a function of the combustion chamber performance such that the synthesis gas produced therewith contains a comparatively high proportion of hydrogen gas at a low combustion chamber power, while it contains a relatively low proportion of hydrogen gas at a comparatively high combustion chamber power ,
- the invention uses the
- synthesis gas with a relatively low proportion of hydrogen gas at high flame temperatures reduces the formation of nitrogen relatively strongly. At the same time, lowering the extinguishing limit is not necessary at high flame temperatures. In contrast, a synthesis gas with a high hydrogen gas content at high flame temperatures would reduce the pollutant emissions, in particular nitrogen oxide emissions. Furthermore, the invention uses the knowledge that at lower flame temperatures, the injection of synthesis gas with a relatively high proportion of hydrogen gas significantly stabilizes the homogeneous combustion reaction by significantly lowering the extinction limit. At the same time, there is no increase in nitrogen oxide formation.
- the operating method according to the invention thus leads to a stabilized operation of the combustion chamber with comparatively small combustion chamber power, for example at low load or partial load, while at the same time with greater combustion chamber power, for example at full load, the pollutant emissions are reduced compared to operation without pilot burner.
- the synthesis gas production of the pilot burner can be controlled by the amount of fuel supplied to the pilot burner, while at the same time the amount of air supplied to the pilot burner is kept constant.
- the hydrogen gas content in the synthesis gas is thus controlled via the fuel / air ratio supplied to the catalytic pilot burner.
- the burner according to the invention is designed so that a larger proportion of the synthesis gas is introduced radially into the burner and / or into the combustion chamber with respect to a longitudinal axis of the respective burner, while a smaller proportion of the synthesis gas with respect to the longitudinal axis axially the burner is introduced or in the combustion chamber. It has been found that with a predominantly radial introduction of the synthesis gas, the best results with regard to pollutant emissions and combustion stabilization can be achieved.
- Fig. 1 is a greatly simplified, principal longitudinal section through a
- Fig. 2a is a longitudinal section as in Fig. 1, but at another
- FIG. 2b shows a cross section through the burner of FIG. 2a
- Fig. 3 is a greatly simplified axial view of an annular combustion chamber according to the invention.
- an inventive burner 1 of a combustion chamber 2 (see Fig. 3) comprises a catalytically operating pilot burner 3.
- the burner 1 comprises a fuel supply 4, which is indicated here only by an arrow and in operation of the burner 1 this supplied with fuel.
- an additional fuel supply 5 is provided, which is likewise symbolized by an arrow and which supplies the pilot burner 3 with fuel during operation of the burner 1.
- an air supply 6 is provided, which is provided jointly for the burner 1 and its pilot burner 3. This common air supply 6 is designed in a manner not further explained in such a way that it distributes the supplied air to the burner 1, see arrows 7, and the pilot burner 3, see arrow 8.
- the burner 1 is used to generate a homogeneous combustion reaction in a combustion chamber 9 of the combustion chamber 2, which is arranged downstream of the burner 1 in the assembled state.
- the combustion chamber 2 in turn serves to generate hot gases for acting on a gas turbine, in particular a power plant.
- the burner 1 also has a mixture forming space 10, which is open in the assembled state to the combustion chamber 9.
- the air supply 6 brings the burner 1 associated air quantity 7 in this mixture forming space 10 a.
- the introduction takes place here in a tangential flow over axially aligned gaps in the burner wall 11, which the mixture formation space 10 circumferentially enveloped with respect to a longitudinal axis 12 of the burner 1.
- the fuel supply 4 supplies the amount of fuel allocated to the burner 1 to the mixture-forming space 10, which is symbolized here by a plurality of arrows 13.
- the fuel supply 4 extends within the burner wall 11. Usually, such a burner 1 is operated lean to achieve the lowest possible combustion reaction in the combustion chamber 9.
- the catalytically operating pilot burner 3 is supplied via the air supply 6, a certain proportion of the total amount of air supplied to the burner 1, namely the partial air amount 8.
- the auxiliary fuel supply 5 is now operated so that a rich fuel / air mixture adjusts to the Pilot burner 3 is supplied.
- Catalyst of the pilot burner 3 a partial oxidation of the fuel, in which a synthesis gas containing hydrogen gas is produced as combustion exhaust gas.
- This synthesis gas is then introduced according to arrows 14 and 15 from the pilot burner 3 into the mixture formation space 10 or into the combustion space 9.
- a part of the synthesis gas with respect to the longitudinal axis 12 is introduced substantially radially into the mixture formation space 10.
- a different part of the synthesis gas with respect to the longitudinal axis 12 is injected substantially axially into the mixture formation space 10 and into the combustion chamber 9, respectively.
- the radially introduced synthesis gas fraction 14 is now greater than the axially introduced synthesis gas fraction 15.
- This particular division of the synthesis gas introduction into the mixture formation space 10 or into the combustion chamber 9 is based on the finding that with the aid of this distribution of the synthesis gas injection, particularly favorable results for a low Nitrogen oxide production and a stabilizing effect for the homogeneous combustion reaction in the combustion chamber 9 can be achieved.
- the pilot burner 3 can be designed, for example, such that at least 50% to 70% of the synthesis gas generated by the pilot burner 3 enters the mixture-forming space 10 radially. Accordingly, the proportion of the synthesis gas, which is introduced axially from the pilot burner 3 into the mixture formation space 10 or into the combustion space 9, is at most 30% to 50%.
- pilot burner 3 it may be expedient to design the pilot burner 3 in addition such that the radially introduced amount of synthesis gas 14 at least partially also has a tangential component with respect to the longitudinal axis 12.
- the pilot burner 3 can have a lance 16.
- the lance 16 extends coaxially with the longitudinal axis 12 of the burner 1. Furthermore, the lance 16 projects axially from a burner head 17 and protrudes into the mixture-forming space 10.
- the lance 16 has corresponding, only partially indicated radial outlet openings 18 and at least one axial outlet opening 19th
- the burner 1 in another embodiment may have a pilot burner 3, which is integrated in the burner wall 11.
- a catalytically active channel is integrated into the burner wall 11 for this purpose.
- a catalyst further upstream and to integrate only the exhaust gas channels in the burner wall 11, which then transport the synthesis gas.
- the burner wall 11 includes a plurality of radial outlet openings 20, through which the larger radial synthesis gas 14 enters the mixture forming space 10.
- the burner wall 11 contains a plurality of axial outlet openings 21, through which then the smaller axial proportion of synthesis gas 15 can be injected into the combustion chamber 9.
- the burner 1 shown in FIG. 2a operates essentially identically to the burner 1 shown in FIG. 1, wherein the radial fuel injection 13 is shown in simplified form in FIG. 2a.
- a combustion chamber 2 which according to the invention is designed as an annular combustion chamber, comprises a plurality of burners 1, which are arranged distributed in an annular manner upstream of the combustion chamber 9, not shown in FIG.
- Each of these burners 1 is equipped with a pilot burner 3, which operates catalytically and can generate the hydrogen gas-containing synthesis gas.
- a common air supply 22 is provided for all burners 1, which is symbolized here by an arrow.
- the burners 1 are usually divided into fuel supply groups. For example, two burner groups are provided to which each half of all burners 1 is assigned. Each burner group has its own fuel supply 23 or 23 '.
- the burners 1 of one group are expediently arranged alternately with the burners 1 of the other group.
- the pilot burners 3 of the one group can be supplied with fuel via a common auxiliary fuel supply 24, while the pilot burners 3 of the other burner group are supplied with fuel via a further common additional fuel supply 24 '.
- the air supply within the individual burners 1 takes place again together, with a constant distribution of the supplied air quantity to the respective burner 1 and the associated pilot burner 3.
- the burners 1 in the combustion chamber 2 can be operated as follows:
- combustion chamber 2 is to produce a comparatively low combustion chamber power, on the one hand the fuel supply 23 or 23 'of the
- Burner 1 reduced accordingly.
- the pilot burners 3 are controlled in such a way that they each generate a synthesis gas which contains a comparatively high proportion of hydrogen gas.
- This synthesis gas is introduced via the pilot burner 3 into the mixture-forming chambers 10 of the burners 1 and into the combustion chamber 9 of the combustion chamber 2, where it causes a lowering of the extinguishing limit due to its high proportion of hydrogen gas.
- the extinction limit was lowered by about 100 K.
- the combustion reaction in the combustion chamber 9 can proceed stably, even if the temperature in the combustion chamber 9 is comparatively low due to the reduced combustion chamber power.
- a low combustion chamber performance is characterized by an exit temperature of the combustion exhaust gases from the combustion chamber 9 of at most 1600 K. The low combustion chamber temperatures do not lead to an increase in nitrogen oxide formation despite the relatively high proportion of hydrogen gas.
- the burners 1 are supplied with a correspondingly increased amount of fuel.
- the pilot burners 3 are controlled so that the synthesis gas generated by them contains a lower proportion of hydrogen gas.
- the increased fuel supply via the burner 1 leads to an increase in the temperature in the combustion chamber 9, whereby the combustion chamber power increases.
- the comparatively low proportion of hydrogen gas in the synthesis gas leads to a significant reduction in nitrogen oxide formation at high combustion chamber temperatures. Accordingly, with the help of syngas injection, the Pollutant emissions are significantly reduced. In the experiment, the nitrogen oxide formation could be reduced by about 33%.
- the synthesis gas injected from the pilot burners 3 contains at the low burner chamber capacity a hydrogen gas content of at least 30% by volume.
- the hydrogen gas content at the low combustor power is between 30% by volume and 50% by volume.
- the hydrogen gas content in the synthesis gas at a high combustion chamber capacity is at most 30% by volume, in particular in a range from 5% by volume to 30% by volume.
- the synthesis gas production or the hydrogen gas fraction in the synthesis gas can be changed particularly easily in the catalytically operating pilot burners 3 by varying the fuel / air ratio.
- This fuel / air ratio can be particularly easy to change by varying the amount of fuel supplied to the pilot burners 3, which is relatively easy to implement.
- the amount of air supplied remains substantially constant, so that expensive control and regulating devices can be dispensed with here.
- the inventive operation of the combustion chamber 2 and its burner 1 ensures that the combustion chamber 2 can be operated comparatively stable at low power, while at high combustion chamber performance, the production of nitrogen oxides can be greatly reduced.
- pilot burners 3 in the burner 1 of the annular combustion chamber 2 has an additional valuable advantage.
- annular combustion chambers 2 there are usually undesirable interactions of the individual burner 1 with each other. These interactions can too Pulsations and thus lead to an undesirable vibration load on the components and to an undesirable noise pollution of the environment.
- the interactions can reduce the stability of the combustion reactions, locally increase the temperature and thus support the formation of nitrogen oxides.
- the amount of air supplied to the individual burners 1 can deviate from an ideal air quantity or set air quantity. Since, as explained above, the distribution of the quantity of air supplied to the individual burner 1 to the burner 1 and its pilot burner 3 is constant, the quantity of air supplied to the individual pilot burner 3 changes in the same proportion as the total quantity of air supplied to the individual burner 1 , If the total amount of air or actual air quantity actually supplied to the individual burner 1 deviates from the desired setpoint air quantity, the quantity of air supplied to the respective pilot burner 3 also changes as a result. Since in a stationary operation of the combustion chamber 2, the amount of fuel supplied to the pilot burner 3 remains constant, a change in the amount of air leads to a change in the fuel / air ratio.
- the fuel / air ratio correlates with the synthesis gas production or with the hydrogen gas content in the synthesis gas generated by the catalytic pilot burners 3.
- the combustion air / fuel ratio increases.
- An increased combustion air / fuel ratio increases the hydrogen gas content in the synthesis gas and leads to an increased exhaust gas temperature of the respective pilot burner 3, ie to an increased synthesis gas temperature.
- the portion of the flame front associated with this burner 1 or this pilot burner 3 is moved upstream in the combustion chamber 9. This local change in position of the flame front increases the pressure drop at this burner 1, that is to say its flow resistance, and as a result leads to a reduction of the quantity of air supplied to this burner 1. In this way, the actual air quantity decreases and approaches the set air quantity.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005061486.8A DE102005061486B4 (de) | 2005-12-22 | 2005-12-22 | Verfahren zum Betreiben einer Brennkammer einer Gasturbine |
PCT/EP2006/069429 WO2007074033A1 (de) | 2005-12-22 | 2006-12-07 | Brennkammer mit brenner und zugehöriges betriebsverfahren |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1963748A1 true EP1963748A1 (de) | 2008-09-03 |
EP1963748B1 EP1963748B1 (de) | 2015-08-05 |
Family
ID=37776558
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06830438.5A Not-in-force EP1963748B1 (de) | 2005-12-22 | 2006-12-07 | Brennkammer mit brenner und zugehöriges betriebsverfahren |
Country Status (5)
Country | Link |
---|---|
US (1) | US7568907B2 (de) |
EP (1) | EP1963748B1 (de) |
DE (1) | DE102005061486B4 (de) |
MY (1) | MY153409A (de) |
WO (1) | WO2007074033A1 (de) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7841180B2 (en) * | 2006-12-19 | 2010-11-30 | General Electric Company | Method and apparatus for controlling combustor operability |
EP2072899B1 (de) | 2007-12-19 | 2016-03-30 | Alstom Technology Ltd | Kraftstoffeinspritzsystem |
US8286594B2 (en) * | 2008-10-16 | 2012-10-16 | Lochinvar, Llc | Gas fired modulating water heating appliance with dual combustion air premix blowers |
EP2299091A1 (de) * | 2009-09-07 | 2011-03-23 | Alstom Technology Ltd | Verfahren zum Umschalten des Betriebes eines Gasturbinenbrenners von flüssigen auf gasförmigen Brennstoff und umgekehrt. |
CH701905A1 (de) * | 2009-09-17 | 2011-03-31 | Alstom Technology Ltd | Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens. |
US11774093B2 (en) | 2020-04-08 | 2023-10-03 | General Electric Company | Burner cooling structures |
JP7435328B2 (ja) | 2020-07-13 | 2024-02-21 | 三浦工業株式会社 | 燃焼装置 |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT1063699B (it) * | 1975-09-16 | 1985-02-11 | Westinghouse Electric Corp | Metodo di avviamento di una turbina a gas di grande potenza con un combustore catalitico |
DE3474714D1 (en) * | 1983-12-07 | 1988-11-24 | Toshiba Kk | Nitrogen oxides decreasing combustion method |
DE4426351B4 (de) * | 1994-07-25 | 2006-04-06 | Alstom | Brennkammer für eine Gasturbine |
DE4439619A1 (de) * | 1994-11-05 | 1996-05-09 | Abb Research Ltd | Verfahren und Vorrichtung zum Betrieb eines Vormischbrenners |
DE19654022A1 (de) * | 1996-12-21 | 1998-06-25 | Abb Research Ltd | Verfahren zum Betrieb einer Gasturbogruppe |
US6358040B1 (en) | 2000-03-17 | 2002-03-19 | Precision Combustion, Inc. | Method and apparatus for a fuel-rich catalytic reactor |
US6415608B1 (en) * | 2000-09-26 | 2002-07-09 | Siemens Westinghouse Power Corporation | Piloted rich-catalytic lean-burn hybrid combustor |
EP1286112A1 (de) * | 2001-08-09 | 2003-02-26 | Siemens Aktiengesellschaft | Vormischbrenner und Verfahren zu dessen Betrieb |
AU2003219845A1 (en) * | 2002-02-22 | 2003-09-09 | Catalytica Energy Systems, Inc. | Catalytically piloted combustion system and methods of operation |
AU2003240374A1 (en) | 2002-08-30 | 2004-03-19 | Alstom Technology Ltd | Hybrid burner and corresponding operating method |
US7421844B2 (en) | 2002-08-30 | 2008-09-09 | Alstom Technology Ltd | Method for the combustion of a fuel-oxidizer mixture |
DE10329162A1 (de) * | 2003-06-27 | 2005-01-13 | Alstom Technology Ltd | Katalytischer Reaktor und zugehöriges Betriebsverfahren |
EP1510761A1 (de) * | 2003-08-13 | 2005-03-02 | Siemens Aktiengesellschaft | Verfahren zur Verbrennung eines fluidischen Brennstoffs sowie Brenner, insbesondere für eine Gasturbine, zur Durchführung des Verfahrens |
EP1568942A1 (de) * | 2004-02-24 | 2005-08-31 | Siemens Aktiengesellschaft | Vormischbrenner sowie Verfahren zur Verbrennung eines niederkalorischen Brenngases |
-
2005
- 2005-12-22 DE DE102005061486.8A patent/DE102005061486B4/de not_active Expired - Fee Related
-
2006
- 2006-12-07 EP EP06830438.5A patent/EP1963748B1/de not_active Not-in-force
- 2006-12-07 WO PCT/EP2006/069429 patent/WO2007074033A1/de active Application Filing
- 2006-12-07 MY MYPI20082219A patent/MY153409A/en unknown
-
2008
- 2008-06-19 US US12/142,299 patent/US7568907B2/en active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2007074033A1 * |
Also Published As
Publication number | Publication date |
---|---|
MY153409A (en) | 2015-02-13 |
EP1963748B1 (de) | 2015-08-05 |
WO2007074033A1 (de) | 2007-07-05 |
US20080314045A1 (en) | 2008-12-25 |
DE102005061486B4 (de) | 2018-07-12 |
DE102005061486A1 (de) | 2007-07-12 |
US7568907B2 (en) | 2009-08-04 |
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