EP0577862A1 - Dispositif de post-combustion - Google Patents

Dispositif de post-combustion Download PDF

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Publication number
EP0577862A1
EP0577862A1 EP92111347A EP92111347A EP0577862A1 EP 0577862 A1 EP0577862 A1 EP 0577862A1 EP 92111347 A EP92111347 A EP 92111347A EP 92111347 A EP92111347 A EP 92111347A EP 0577862 A1 EP0577862 A1 EP 0577862A1
Authority
EP
European Patent Office
Prior art keywords
afterburner
damping
combustion chamber
resonator
air
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
Application number
EP92111347A
Other languages
German (de)
English (en)
Other versions
EP0577862B1 (fr
Inventor
Jakob Prof. Dr. Keller
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.)
ABB RESEARCH Ltd
Original Assignee
ABB Research Ltd Switzerland
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 ABB Research Ltd Switzerland filed Critical ABB Research Ltd Switzerland
Priority to EP92111347A priority Critical patent/EP0577862B1/fr
Priority to DE59208193T priority patent/DE59208193D1/de
Priority to US08/078,031 priority patent/US5431018A/en
Priority to CA002098810A priority patent/CA2098810A1/fr
Priority to JP5164642A priority patent/JPH0694227A/ja
Priority to KR1019930012484A priority patent/KR940002550A/ko
Publication of EP0577862A1 publication Critical patent/EP0577862A1/fr
Application granted granted Critical
Publication of EP0577862B1 publication Critical patent/EP0577862B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • 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
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the invention relates to an afterburner for a gas turbine combustion chamber, for example, in which a fuel feed arranged in a combustion chamber wall is enclosed by an annular air duct.
  • Afterburner in gas turbine combustors are used to advantage when very low-emission oil or gas combustion is aimed for.
  • the gas flow downstream of the normal burner, into which fuel has already been introduced from a primary source can have an average temperature of approximately 850 ° C.
  • fuel that is injected through an afterburner can be ignited sufficiently quickly.
  • the ignition delay time is so short that the post-combustion process is initiated over a useful distance, for example 2 to 10 cm.
  • afterburners are not self-sufficient. A flame stabilization zone is intentionally avoided here.
  • An afterburner thus offers the possibility of also at very high speeds, i.e. to convert a lot of fuel in very short periods of time. Your advantage is that the time spent in a zone that is not perfectly pre-mixed can be kept almost as short as you like. It can therefore be mixed very quickly at high speed.
  • the fuel or an air-fuel mixture from the afterburner is usually blown into the afterburner chamber with a cross jet, where it is mixed in quickly and homogeneously. This is not possible with conventional burners, otherwise the flame stabilization required there would be lost.
  • the predominant problem with an afterburner is that it is very susceptible to vibration. This is due to the fact that there is no clearly defined reaction zone as in a normal burner. Because the reaction zones can easily be influenced by pressure disturbances, such pressure disturbances in the combustion chamber can lead to large-scale displacements of the reaction, which can lead to very strong vibrations.
  • the invention has for its object to dampen thermoacoustically fanned vibrations in an afterburner of the type mentioned.
  • the air duct communicates with a flow-through Helmholz resonator via at least one feed pipe, the outlet of the at least one damping pipe of the Helmholz resonator being located in the area of the burner mouth into the afterburner.
  • the damping system can be effectively integrated into the afterburner, and because of the simple construction of an afterburner it is possible to design the afterburner itself or parts thereof as a damper.
  • the damping tube is designed as an annular channel.
  • the afterburner is thus encased in an air curtain that comes from the Helmholz resonator.
  • the damping medium flowing out of the damping tube in a ring shape into the afterburning chamber is therefore a component of the afterburning air.
  • the air used for damping purposes is therefore not considered lost.
  • a Nac burner arranged in a combustion chamber wall 1 is shown in simplified form in FIG.
  • the fuel is injected into the afterburning chamber 9 via an oil line 2 arranged centrally in the burner and / or via an annular gas lance 3 which surrounds the oil line 2.
  • the intention is, on the one hand, to fuel the gas very quickly into the existing gas volume to interfere, on the other hand to delay the reaction as long as possible. This avoids that very hot zones prevail over longer time intervals before the mixing process is complete.
  • the injected fuel jet is enveloped by an air jacket. This air jacket is brought up to the burner mouth 8 via an air duct 4.
  • the air duct 4 is fed from the collecting space 10 downstream of the compressor, not shown, and surrounds the fuel feeds 2, 3 in a ring.
  • This air jacket which conducts the post-combustion air that is usually required into the combustion chamber 9, also cools the fuel supply lines 2, 3.
  • a rinsed Helmholtz resonator is now to be used for sound attenuation.
  • a volume enclosing the air duct 4 is arranged in the combustion chamber wall 1, so that the afterburner and Helmholtz resonator form an integral component.
  • the air inlet openings to the helmwood volume 6 are designed as supply pipes 5, several of which extend over the circumference from the outer wall of the air duct 4 and protrude into the volume 6.
  • the damping tube 7 of the Helmholtz resonator is designed as an annular channel.
  • the feed tubes 5 preferably have the same length as the damper tube 7.
  • the ends of the damper tube are rounded off at the inlet and outlet.
  • the exit of the annular damper tube is located in the immediate area of the burner mouth 8, so that it is encased by a further annular air curtain.
  • the location of the damping is decisive for the stabilization of a thermoacoustic oscillation.
  • the greatest increase occurs when the reaction rate and the pressure disturbance oscillate in phase.
  • the strongest reaction rate usually occurs near the center of the combustion zone.
  • the ring-shaped arrangement of the damping tube in the region of the mouth of the afterburner therefore has the effect that the damping effect is achieved at an optimal point.
  • the feed pipes 5 are dimensioned such that they cause a relatively high pressure drop for the inflowing air.
  • the limitation of the pressure drop in the damping pipes results from the requirement that even with uneven pressure distribution on the inside of the combustion chamber wall, a sufficient purge air flow into the afterburning chamber is always guaranteed.
  • hot gas must not enter the Helmholz resonator in the opposite direction at any point.
  • the average flow velocity in the damping tube in the present case of a gas turbine combustion chamber can typically be 2 to 4 m / s with an ideal design. So it is very small compared to the vibration amplitude, which means that the air particles move back and forth pulsating in the damping tube. Nevertheless, only enough air is allowed to flow through that a significant heating of the resonator is avoided. Because with larger amounts of air, the resonance and thus the damping become weaker.
  • the Helmholz resonator is therefore dimensioned so that adequate purging is guaranteed. This prevents the damper from heating up and the resulting damper frequency drifting away.
  • the choice of the size of the Helmholtz volume 6 results from the requirement that the phase angle between the fluctuations in the damping air mass flows through the supply and Damping pipes should be greater than or equal to ⁇ / 2.
  • this requirement means that the volume should be at least so large that the Helmholtz frequency of the resonator, which is formed by the volume 6 and the openings 5 and 7, at least the frequency of the combustion chamber vibration to be damped.
  • the volume of the Helmholtz resonator used is preferably designed for the lowest natural frequency of the afterburner. It is also possible to choose an even larger volume. It is thereby achieved that a pressure fluctuation on the inside of the afterburning space leads to a strongly opposite phase fluctuation of the air mass flow, because the fluctuations in the damping air mass flows through the supply pipes and the damping pipes are no longer in phase.
  • the basic features of a flow through a Helmholtz resonator as can be used in a combustion chamber, but also everywhere else, are shown in FIG. 2.
  • the resonator essentially consists of the feed pipe 5a, the resonance volume 6a and the damping pipe 7a.
  • the feed pipe 5a determines the pressure drop.
  • the speed at the end of the feed pipe is adjusted so that the dynamic pressure of the jet together with the losses corresponds to the pressure drop across the combustion chamber. Only enough air is supplied that the interior of the damper does not heat up. Heating by radiation from the area of the combustion chamber would result in the frequency not remaining stable. The flushing should therefore only dissipate the radiated heat. So far, Helmholtz resonators are known.

Landscapes

  • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)
EP92111347A 1992-07-03 1992-07-03 Dispositif de post-combustion Expired - Lifetime EP0577862B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP92111347A EP0577862B1 (fr) 1992-07-03 1992-07-03 Dispositif de post-combustion
DE59208193T DE59208193D1 (de) 1992-07-03 1992-07-03 Nachbrenner
US08/078,031 US5431018A (en) 1992-07-03 1993-06-18 Secondary burner having a through-flow helmholtz resonator
CA002098810A CA2098810A1 (fr) 1992-07-03 1993-06-18 Bruleur secondaire
JP5164642A JPH0694227A (ja) 1992-07-03 1993-07-02 二次バーナ
KR1019930012484A KR940002550A (ko) 1992-07-03 1993-07-03 이차 버너

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92111347A EP0577862B1 (fr) 1992-07-03 1992-07-03 Dispositif de post-combustion

Publications (2)

Publication Number Publication Date
EP0577862A1 true EP0577862A1 (fr) 1994-01-12
EP0577862B1 EP0577862B1 (fr) 1997-03-12

Family

ID=8209779

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92111347A Expired - Lifetime EP0577862B1 (fr) 1992-07-03 1992-07-03 Dispositif de post-combustion

Country Status (6)

Country Link
US (1) US5431018A (fr)
EP (1) EP0577862B1 (fr)
JP (1) JPH0694227A (fr)
KR (1) KR940002550A (fr)
CA (1) CA2098810A1 (fr)
DE (1) DE59208193D1 (fr)

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EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
KR100905254B1 (ko) 2007-11-06 2009-06-29 홍정구 연소기의 불안정 연소 영역에 대한 저감장치 및 저감방법
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
EP2474784A1 (fr) 2011-01-07 2012-07-11 Siemens Aktiengesellschaft Système de combustion pour turbine à gaz comprenant un résonateur
EP2642203A1 (fr) * 2012-03-20 2013-09-25 Alstom Technology Ltd Amortisseur de helmholtz annulaire
WO2014131876A1 (fr) * 2013-02-28 2014-09-04 Siemens Aktiengesellschaft Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques
US9022726B2 (en) 2010-06-25 2015-05-05 Alstom Technology Ltd Thermally loaded, cooled component
EP3306197A1 (fr) * 2016-10-08 2018-04-11 Ansaldo Energia Switzerland AG Buse concentrique de carburant double pour turbine à gaz
EP3438540A1 (fr) * 2017-07-31 2019-02-06 Siemens Aktiengesellschaft Brûleur comprenant un amortisseur acoustique

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DE59809097D1 (de) 1998-09-30 2003-08-28 Alstom Switzerland Ltd Brennkammer für eine Gasturbine
DE19905995A1 (de) 1999-02-15 2000-08-17 Asea Brown Boveri Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer sowie Verfahren zum Betrieb einer solchen Brennstofflanze
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US6351947B1 (en) 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
DE10056243A1 (de) * 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
RU2212589C1 (ru) * 2002-06-28 2003-09-20 Козырев Александр Валентинович Камера сгорания теплового двигателя
RU2229614C1 (ru) * 2002-12-15 2004-05-27 Андреев Анатолий Васильевич Форсажная камера газотурбинного двигателя (варианты)
RU2229615C1 (ru) * 2002-12-15 2004-05-27 Андреев Анатолий Васильевич Форсажная камера газотурбинного двигателя
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EP1601913A1 (fr) * 2003-03-07 2005-12-07 Alstom Technology Ltd Bruleur de premelange
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US7788926B2 (en) * 2006-08-18 2010-09-07 Siemens Energy, Inc. Resonator device at junction of combustor and combustion chamber
US8127546B2 (en) * 2007-05-31 2012-03-06 Solar Turbines Inc. Turbine engine fuel injector with helmholtz resonators
US8516819B2 (en) 2008-07-16 2013-08-27 Siemens Energy, Inc. Forward-section resonator for high frequency dynamic damping
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US8789372B2 (en) 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator
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WO2011036205A1 (fr) * 2009-09-24 2011-03-31 Siemens Aktiengesellschaft Système de tuyautage à combustible, procédé de fonctionnement d'une turbine à gaz et procédé de balayage du système de tuyautage à combustible d'une turbine à gaz
WO2011054766A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection de brûleur de postcombustion
WO2011054757A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage avec lances à combustible
WO2011054771A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Brûleur à prémélange pour chambre de combustion de turbine à gaz
WO2011054739A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage
WO2011054760A1 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système de refroidissement permettant d'accroître le rendement d'une turbine à gaz
US9127837B2 (en) * 2010-06-22 2015-09-08 Carrier Corporation Low pressure drop, low NOx, induced draft gas heaters
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US20180174566A1 (en) * 2016-12-19 2018-06-21 Caterpillar Inc. Compact acoustic resonator for enclosed systems
EP3354984B1 (fr) 2017-01-31 2020-09-09 Ansaldo Energia Switzerland AG Injecteur à lobes pour une chambre de combustion de turbine à gaz
CN114165813B (zh) * 2021-12-03 2022-08-30 北京航空航天大学 一种双油路供油的气动辅助一体化支板稳定器
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FR2570129A1 (fr) * 1984-09-05 1986-03-14 Messerschmitt Boelkow Blohm Dispositif pour amortir les vibrations dans la chambre de combustion de moteurs-fusees a propergols liquides

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CH262382A (de) * 1944-11-28 1949-06-30 Vickers Electrical Co Ltd Verbrennungsturbinenanlage.
GB648699A (en) * 1947-10-17 1951-01-10 Arthur Holmes Fletcher Improvements in or relating to gas-turbine engine fuel systems and liquid fuel injectors therefor
FR2414126A1 (fr) * 1978-01-04 1979-08-03 United Kingdom Government Melangeur de carburant par injection de ce dernier dans un jet d'air
US4409787A (en) * 1979-04-30 1983-10-18 General Electric Company Acoustically tuned combustor
DE3324805A1 (de) * 1983-07-09 1985-01-17 Betriebsforschungsinstitut VDEh - Institut für angewandte Forschung GmbH, 4000 Düsseldorf Einrichtung zur vermeidung von druckschwingungen bei brennkammern
FR2570129A1 (fr) * 1984-09-05 1986-03-14 Messerschmitt Boelkow Blohm Dispositif pour amortir les vibrations dans la chambre de combustion de moteurs-fusees a propergols liquides

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Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
WO2003074936A1 (fr) * 2002-03-07 2003-09-12 Siemens Aktiengesellschaft Turbine a gaz
CN1320314C (zh) * 2002-03-07 2007-06-06 西门子公司 燃气轮机
US7246493B2 (en) 2002-03-07 2007-07-24 Siemens Aktiengesellschaft Gas turbine
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EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
EP2400115B1 (fr) * 2010-06-25 2019-05-29 Ansaldo Energia Switzerland AG Composant chargé de chaleur refroidi
US9022726B2 (en) 2010-06-25 2015-05-05 Alstom Technology Ltd Thermally loaded, cooled component
EP2474784A1 (fr) 2011-01-07 2012-07-11 Siemens Aktiengesellschaft Système de combustion pour turbine à gaz comprenant un résonateur
WO2012093011A1 (fr) 2011-01-07 2012-07-12 Siemens Aktiengesellschaft Système de combustion pour turbine à gaz comprenant un résonateur
WO2013139813A1 (fr) * 2012-03-20 2013-09-26 Alstom Technology Ltd Amortisseur de helmholtz annulaire
EP2642203A1 (fr) * 2012-03-20 2013-09-25 Alstom Technology Ltd Amortisseur de helmholtz annulaire
CN104204675A (zh) * 2012-03-20 2014-12-10 阿尔斯通技术有限公司 环形赫尔姆霍茨阻尼器
US9618206B2 (en) 2012-03-20 2017-04-11 General Electric Technology Gmbh Annular helmholtz damper
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WO2014131876A1 (fr) * 2013-02-28 2014-09-04 Siemens Aktiengesellschaft Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques
EP3306197A1 (fr) * 2016-10-08 2018-04-11 Ansaldo Energia Switzerland AG Buse concentrique de carburant double pour turbine à gaz
US10753615B2 (en) 2016-10-08 2020-08-25 Ansaldo Energia Switzerland AG Dual fuel concentric nozzle for a gas turbine
EP3438540A1 (fr) * 2017-07-31 2019-02-06 Siemens Aktiengesellschaft Brûleur comprenant un amortisseur acoustique
WO2019025094A1 (fr) * 2017-07-31 2019-02-07 Siemens Aktiengesellschaft Brûleur comprenant un amortisseur acoustique
US11204166B2 (en) 2017-07-31 2021-12-21 Siemens Energy Global GmbH & Co. KG Burner including an acoustic damper

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JPH0694227A (ja) 1994-04-05
DE59208193D1 (de) 1997-04-17
EP0577862B1 (fr) 1997-03-12
US5431018A (en) 1995-07-11
CA2098810A1 (fr) 1994-01-04
KR940002550A (ko) 1994-02-17

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