EP2295858A1 - Stabilisierung der Flamme eines Brenners - Google Patents

Stabilisierung der Flamme eines Brenners Download PDF

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Publication number
EP2295858A1
EP2295858A1 EP09167055A EP09167055A EP2295858A1 EP 2295858 A1 EP2295858 A1 EP 2295858A1 EP 09167055 A EP09167055 A EP 09167055A EP 09167055 A EP09167055 A EP 09167055A EP 2295858 A1 EP2295858 A1 EP 2295858A1
Authority
EP
European Patent Office
Prior art keywords
fluid
jet
burner
reaction space
burner according
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Withdrawn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
EP09167055A
Other languages
German (de)
English (en)
French (fr)
Inventor
Matthias Hase
Werner Krebs
Bernd 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 EP09167055A priority Critical patent/EP2295858A1/de
Priority to US13/388,304 priority patent/US9074762B2/en
Priority to EP10740607.6A priority patent/EP2462379B1/de
Priority to CN201080034454.0A priority patent/CN102472485B/zh
Priority to PCT/EP2010/061201 priority patent/WO2011015549A1/de
Priority to RU2012108126/06A priority patent/RU2533609C2/ru
Publication of EP2295858A1 publication Critical patent/EP2295858A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/48—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous 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
    • 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
    • F23C2202/20—Premixing fluegas with fuel
    • 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
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the present invention relates to a burner for stabilizing the flame of a gas turbine, which comprises a reaction space and several opening into the reaction chamber jet nozzles, wherein the jet nozzles by means of a fluid jet fluid is injected into the reaction space, wherein the fluid is burned in the reaction space to hot gas, and a method for stabilizing the flame of a burner of a gas turbine.
  • Beam flame-based combustion systems offer advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view.
  • By a suitable choice of the beam pulse small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus suppress pressure pulsations which are typical for spin-stabilized flames.
  • the jet flames are stabilized by mixing in hot recirculating gases.
  • the required temperatures of the recirculation zone can not be guaranteed in gas turbines, especially in the lower part load range, by the known ring arrangement of the beams with a central recirculation zone.
  • the stabilization of a jet flame therefore remains an incompletely solved task.
  • Another object of the present invention is to provide an advantageous burner of a gas turbine for stabilizing the flame of such a burner. Another object of the present invention is to provide an advantageous To provide methods for stabilizing the flame of such a burner.
  • the torch-related object is achieved by a burner for stabilizing the flame of a burner of a gas turbine according to claim 1.
  • the object related to the method is achieved by specifying a method according to claim 16.
  • the dependent claims contain further, advantageous embodiments of the invention.
  • the burner according to the invention of a gas turbine comprises a reaction space and a plurality of jet nozzles opening into the reaction space.
  • the jet nozzles With the jet nozzles, fluid is injected into the reaction space by means of a fluid jet. The fluid in the reaction space is then burned to hot gas.
  • the invention has recognized that the jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction.
  • At least one jet nozzle now has an annular gap which is arranged around the fluid jet. This sucks a portion of the hot gas from the reaction space, so that it flows against the fluid flow direction in the annular gap. According to the invention, the hot gas is now mixed with the fluid jet within the jet nozzle.
  • the annular gap is formed by means of an insert tube.
  • the sucked gases can have a high temperature, which can damage the burner under certain circumstances.
  • the insert tube is at least partially made of high quality materials with and without coating, e.g. designed as a ceramic version with and without coating.
  • the insert tube has at least one opening in order to inject the hot gas into the fluid jet.
  • the at least one opening is arranged upstream.
  • the hot gas is sucked through the annular gap directly into the nozzle and is injected through the openings in the fluid jet.
  • the openings are therefore mounted in the directly limiting the fluid jet wall.
  • the size of the openings and the height of the annular gap are designed so that a good hot gas mixing in the air or the air / fuel mixture is ensured in the jet nozzle and that in the partial load range, the mixture temperature is brought to a value that ensures reliable ignition ,
  • the openings can be designed as a bore or slots, which can also be made at an angle.
  • the insert tube at the upstream end to a thickening. If compressor air, with or without fuel, passes the feed tube past the nozzle to the nozzle, deflection losses can thus be avoided.
  • the thickening is diffused in the flow direction. Thus, an increase in the static pressure difference between the combustion chamber and the fluid flowing in the nozzle at high speed can be effected.
  • the insert tube is preferably designed to be diffused in the flow direction in the flow direction.
  • an increase in the static pressure difference between the combustion chamber and the fluid flowing in the nozzle at high speed can also be effected.
  • a second annular channel for guiding combustion air and / or fuel is provided around the insert tube.
  • means for increasing the heat transfer are provided in the second annular channel.
  • these agents are dimples and / or cooling fins and / or wings.
  • all other cooling concepts such as impingement cooling, convective cooling are also conceivable in which the compressor air or the compressor / fuel mixture is added to the reaction space.
  • the cooling air flowing through the second annular channel and / or fuel cools the insert tube thus fluid downstream.
  • the jet nozzle has a nozzle outlet with a diameter D.
  • the nozzle outlet is offset from the annular gap in the flow direction.
  • the offset comprises a length of 0-3 x D, where D is the diameter D of the nozzle outlet. This ensures optimum intake, especially in partial load operation.
  • the fluid is compressor air which is premixed with fuel, partially premixed, or non-premixed.
  • the object related to the method is achieved by specifying a method for stabilizing the flame of a burner of a gas turbine, which comprises a reaction space and a plurality of jet nozzles opening into the reaction space, wherein the jet nozzles by means of a fluid jet fluid in the Reaction space is injected, wherein the fluid is burned in the reaction space, whereby a hot gas is formed.
  • a method for stabilizing the flame of a burner of a gas turbine which comprises a reaction space and a plurality of jet nozzles opening into the reaction space, wherein the jet nozzles by means of a fluid jet fluid in the Reaction space is injected, wherein the fluid is burned in the reaction space, whereby a hot gas is formed.
  • at least one jet nozzle has an annular gap through which the hot gas is partially sucked in and flows against the fluid flow direction into the annular gap and is mixed with the fluid jet within the jet nozzle.
  • the fluid preferably flows into the reaction space at high speed.
  • a pressure difference is formed between the reaction space and the fluid jet flowing into the reaction space.
  • the fluid is formed at partial load operation of the burner from a fuel / compressor air mixture, and at full load from compressor air, which has only slightly or no fuel content.
  • These nozzles thus act in partial load operation as a pilot burner with pilot beams.
  • pilot beams are made smaller than the other beams, so that less air passes through these nozzles.
  • a stabilization is guaranteed at partial load operation.
  • the burner is configured with a plurality of jet nozzles, of which, however, only one or a few nozzles according to the invention are. These then act as "pilot" at partial load as described above and are supplied with little or no fuel during full-load operation. This avoids that increased NOx values occur during base load operation.
  • FIG. 1 shows a section of a gas turbine with a shaft 14 arranged along a shaft axis and not shown, and a parallel to the shaft axis 14 aligned combustion chamber 16 in a longitudinal section.
  • the combustion chamber 16 is rotationally symmetrical about a combustion chamber axis 18.
  • the combustion chamber axis 18 is arranged in this particular embodiment parallel to the shaft axis 14, wherein it can also run at an angle to the shaft axis 14, in extreme cases perpendicular to this.
  • An annular housing 10 of the combustion chamber 16 surrounds a reaction space 5, which is likewise designed rotationally symmetrical about the combustion chamber axis 18.
  • FIG. 2 schematically shows a section through a jet burner perpendicular to a shaft axis 14 of the burner.
  • the burner comprises a housing 10 which has a circular cross-section. Within the housing 10, a certain number of jet nozzles 3 is arranged substantially annular. Each jet nozzle 3 has a circular cross section.
  • the burner may include a pilot burner 25.
  • FIG. 3 schematically shows a section through another jet burner, wherein the section is perpendicular to the central axis of the further burner.
  • the burner also has a housing 10 which has a circular cross-section and in which a number of inner and outer jet nozzles 3,30 is arranged.
  • the jet nozzles 3, 30 each have a circular cross-section, the outer jet nozzles 3 having an equal or larger cross-sectional area than the inner jet nozzles 30.
  • the outer jet nozzles 3 are arranged essentially annularly inside the housing 10 and form an outer ring.
  • the inner jet nozzles 30 are also arranged annularly within the housing 10.
  • the inner jet nozzles 30 form an inner ring that is concentric with the outer jet nozzle ring.
  • FIGS. 2 and 3 merely show examples of the arrangement of jet nozzles 3, 30 within a jet burner. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 3,30 possible.
  • the jet flame-based combustion system offers advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view.
  • By a suitable choice of the beam pulse small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus pressure pulsations, which are typical of spin-stabilizing flames, suppress.
  • the jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction. This is achieved by means of the invention now.
  • Fig. 4 shows a jet nozzle 6 according to the invention.
  • the burner comprises a reaction space 5 and a plurality of jet nozzles 6 opening into the reaction space 5.
  • the jet nozzle By means of the jet nozzle, fluid is injected into the reaction space 5 with a fluid jet 2.
  • the fluid In the reaction space 5, the fluid is burned to hot gas 4.
  • the fluid may be a fuel / air mixture, or even be formed from compressor air.
  • annular gap is now available. This is formed from an insert tube 12.
  • the annular gap 8 is thus arranged around the fluid jet 2.
  • Hot gas 4 is now sucked into the nozzle 6 through this annular gap 8.
  • the particular static pressure difference between the combustion chamber 16 and the reaction space 5 and the fluid flowing at high speed fluid is used, which has a lowered static pressure due to the high flow rates.
  • the annular gap 8 now hot gas 4 flows against the flow direction of the fluid jet 2 in the nozzle 6 in the nozzle 6 back. There, the hot gas 4 is mixed with the fluid jet 2.
  • the hot gas admixture is thus according to the invention within the nozzle 6. This corresponds to a defined mixing of hot gas in the nozzle 6, whereby a reliable ignition and thus a reliable stabilization of the entire burner is ensured.
  • the stabilization is particularly advantageous at partial load operation.
  • only one or a few nozzles 6 of a jet burner can be configured with this device for the suction of hot gas 4. These can act as pilot burners at partial load operation.
  • the fluid may be a fuel / air mixture.
  • these "pilot beams" are made smaller than the other beams, so that less compressor air passes through these nozzles 6.
  • the fluid can then consist essentially of compressor air. Thus, increased NOx levels can be avoided at base load.
  • the hot gas is sucked in through the annular gap 8. This is formed by an insert tube 12. Upstream in the insert tube 12, one or more openings 11 are formed, by means of which the hot gas 4 can be added to the fluid jet 2.
  • the openings 11 are in the insert tube 12 on the beam side, that is arranged in the beam limiting wall.
  • the openings 11 can be designed as bores.
  • the size of the openings 11 and the radial height H of the annular gap 8 are designed so that a good hot gas mixing is ensured in the fluid jet 2 in the jet nozzle 6.
  • the nozzle 6 also has a nozzle outlet 22 with a diameter D.
  • the nozzle outlet 22 can be arranged opposite the annular gap 8 offset in the flow direction.
  • the offset 24 has a length L of 0mm-3x D (mm), where D is the diameter of the nozzle outlet 22.
  • the mixture temperature is brought to a value that ensures reliable ignition and thus a reliable stabilization of the entire burner in all driving ranges.
  • the fluid jet 2 may consist of an air / fuel mixture of different mixing quality.
  • the jet flame itself can be premixed, partially premixed or non-premixed.
  • Fig. 5 shows a further second embodiment of a nozzle 6a according to the invention.
  • a second annular channel 20 is present, which is arranged around the annular gap 8 around.
  • This annular channel 20 can essentially be designed to guide the compressor air or the air / fuel mixture to the nozzle inlet 28.
  • the combustion air or the fuel / air mixture can serve for cooling particularly the radially outer wall of the insert tube 12. This is advantageous because the aspirated gases have a high temperature which otherwise could potentially damage the burner.
  • the annular channel 20 may also be designed with heat transfer increasing measures.
  • the hot gas-carrying passages so in particular the insert tube 12 made of high-quality materials, e.g. be made of ceramic or Keramikent ambiencen materials, the materials may still be coated.
  • Fig. 6 and Fig. 7 show further embodiments of a nozzle according to the invention 6b and 6c. These show nozzles, which in particular the static pressure difference between the combustion chamber 16 or increase the reaction space 5 and the fluid jet flow 2 in the amount of mixing point.
  • Fig. 6 shows an insert tube 12a, which has a thickening 15 at the upstream end.
  • the thickening 15 is executed rounded.
  • the thickening 15 may be formed diffusely 16 in the flow direction. This results in a particularly efficient pressure difference increase.
  • the openings 11 can also be designed as slots, which are optionally provided obliquely to.
  • Fig. 7 has a nozzle 6c, in which the insert tube 12b is formed in the flow direction diffused 21 fluid flow side. Again, there is a particularly efficient pressure difference increase.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)
EP09167055A 2009-08-03 2009-08-03 Stabilisierung der Flamme eines Brenners Withdrawn EP2295858A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP09167055A EP2295858A1 (de) 2009-08-03 2009-08-03 Stabilisierung der Flamme eines Brenners
US13/388,304 US9074762B2 (en) 2009-08-03 2010-08-02 Stabilizing the flame of a burner
EP10740607.6A EP2462379B1 (de) 2009-08-03 2010-08-02 Stabilisierung der flamme eines brenners
CN201080034454.0A CN102472485B (zh) 2009-08-03 2010-08-02 对燃烧器火焰的稳定
PCT/EP2010/061201 WO2011015549A1 (de) 2009-08-03 2010-08-02 Stabilisierung der flamme eines brenners
RU2012108126/06A RU2533609C2 (ru) 2009-08-03 2010-08-02 Стабилизация пламени горелки

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09167055A EP2295858A1 (de) 2009-08-03 2009-08-03 Stabilisierung der Flamme eines Brenners

Publications (1)

Publication Number Publication Date
EP2295858A1 true EP2295858A1 (de) 2011-03-16

Family

ID=41479366

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09167055A Withdrawn EP2295858A1 (de) 2009-08-03 2009-08-03 Stabilisierung der Flamme eines Brenners
EP10740607.6A Not-in-force EP2462379B1 (de) 2009-08-03 2010-08-02 Stabilisierung der flamme eines brenners

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10740607.6A Not-in-force EP2462379B1 (de) 2009-08-03 2010-08-02 Stabilisierung der flamme eines brenners

Country Status (5)

Country Link
US (1) US9074762B2 (zh)
EP (2) EP2295858A1 (zh)
CN (1) CN102472485B (zh)
RU (1) RU2533609C2 (zh)
WO (1) WO2011015549A1 (zh)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140270731A1 (en) * 2013-03-12 2014-09-18 Applied Materials, Inc. Thermal management apparatus for solid state light source arrays
FR3018900B1 (fr) * 2014-03-19 2016-04-15 Yahtec Dispositif de bruleur a pre melange gaz
WO2015154969A1 (en) 2014-04-10 2015-10-15 Sofinter S.P.A. Burner
CN106895399A (zh) * 2017-04-25 2017-06-27 武建斌 一种醇基燃料锅炉内部用气化燃烧装置
CN109028043A (zh) * 2018-06-28 2018-12-18 广州市艾欣能能源科技有限责任公司 一种高效节能的锅炉

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19505614A1 (de) * 1995-02-18 1996-08-22 Abb Management Ag Verfahren zum Betrieb eines Vormischbrenners
EP1950494A1 (de) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Brennkammer für eine Gasturbine

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US2918117A (en) * 1956-10-04 1959-12-22 Petro Chem Process Company Inc Heavy fuel burner with combustion gas recirculating means
US3174526A (en) * 1960-08-23 1965-03-23 Linde Robert Albert Von Atomizing burner unit
BE795261A (fr) * 1972-02-10 1973-05-29 Bailey Frank W Bruleurs canon a retention de flamme bleue et systemes d'echangeur de chaleur
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US4004875A (en) * 1975-01-23 1977-01-25 John Zink Company Low nox burner
DE3033988C2 (de) * 1980-09-10 1986-04-17 Karl-Friedrich Dipl.-Ing. Dipl.-Wirtsch.-Ing. 4100 Duisburg Schmid Gasbrenner mit integrierter Brennerkopf-Luftkühlung
DE3902601A1 (de) * 1989-01-28 1990-08-09 Buderus Heiztechnik Gmbh Gasgeblaesebrenner
RU2008559C1 (ru) * 1991-04-15 1994-02-28 Шестаков Николай Сергеевич Способ сжигания газа и устройство для его осуществления
US5240409A (en) * 1992-04-10 1993-08-31 Institute Of Gas Technology Premixed fuel/air burners
US5350293A (en) * 1993-07-20 1994-09-27 Institute Of Gas Technology Method for two-stage combustion utilizing forced internal recirculation
RU2093750C1 (ru) * 1995-03-09 1997-10-20 Самарский государственный технический университет Способ сжигания топливного газа и устройство для его осуществления
EP0911076A1 (en) * 1997-10-23 1999-04-28 Haldor Topsoe A/S Reformer furnace with internal recirculation
JP3924136B2 (ja) * 2001-06-27 2007-06-06 三菱重工業株式会社 ガスタービン燃焼器
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SE0202836D0 (sv) * 2002-09-25 2002-09-25 Linde Ag Method and apparatus for heat treatment
JP4422104B2 (ja) * 2003-12-16 2010-02-24 株式会社日立製作所 ガスタービン用燃焼器
EP2372245A1 (de) * 2010-03-26 2011-10-05 Siemens Aktiengesellschaft Brenner zur Stabilisierung der Verbrennung einer Gasturbine sowie Verfahren
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19505614A1 (de) * 1995-02-18 1996-08-22 Abb Management Ag Verfahren zum Betrieb eines Vormischbrenners
EP1950494A1 (de) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Brennkammer für eine Gasturbine

Also Published As

Publication number Publication date
EP2462379B1 (de) 2016-03-30
CN102472485B (zh) 2015-02-18
US9074762B2 (en) 2015-07-07
CN102472485A (zh) 2012-05-23
RU2012108126A (ru) 2013-09-10
RU2533609C2 (ru) 2014-11-20
WO2011015549A1 (de) 2011-02-10
EP2462379A1 (de) 2012-06-13
US20120186265A1 (en) 2012-07-26

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