EP0892219A1 - Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz - Google Patents

Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz Download PDF

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Publication number
EP0892219A1
EP0892219A1 EP97810491A EP97810491A EP0892219A1 EP 0892219 A1 EP0892219 A1 EP 0892219A1 EP 97810491 A EP97810491 A EP 97810491A EP 97810491 A EP97810491 A EP 97810491A EP 0892219 A1 EP0892219 A1 EP 0892219A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
mixing device
pressure fluctuation
entropy
wave
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
EP97810491A
Other languages
German (de)
English (en)
Other versions
EP0892219B1 (fr
Inventor
Klaus Dr. Döbbeling
Christian Dr. Paschereit
Wolfgang Dr. Polifke
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.)
General Electric Switzerland GmbH
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 DE59708564T priority Critical patent/DE59708564D1/de
Priority to EP97810491A priority patent/EP0892219B1/fr
Priority to AT97810491T priority patent/ATE226708T1/de
Priority to US09/111,869 priority patent/US6170265B1/en
Publication of EP0892219A1 publication Critical patent/EP0892219A1/fr
Application granted granted Critical
Publication of EP0892219B1 publication Critical patent/EP0892219B1/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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • 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 gas turbine comprising a device for fuel injection, which injects fuel into a mixing device, the injected fuel being mixed with combustion air in the mixing device.
  • the gas turbine also has a combustion chamber arranged downstream of the mixing device, the length of the combustion chamber being L BK and the length of the mixing device L Mix .
  • thermoacoustic Vibrations mutually rocking thermal and acoustic disturbances. It can be high Vibration amplitudes occur that lead to undesirable effects, such as a high mechanical load on the combustion chamber, increased emissions due to inhomogeneous combustion and can even cause the flame to go out.
  • the cooling air flowing into the combustion chamber has an important function in conventional combustion chambers, since the cooling air film on the combustion chamber wall has a sound-damping effect.
  • modern gas turbines in order to achieve the lowest possible NO x emissions, almost the entire proportion of the air is passed through the burner itself, so the proportion for film cooling of the combustion chamber is reduced.
  • the cooling air thus largely fails as a steamer of acoustic and thermoacoustic vibrations.
  • the invention is therefore based on the object, if possible simple and with the least possible design effort and to provide additional space associated process, with the unwanted thermoacoustic vibrations in gas turbine combustion chambers can be minimized.
  • this object is achieved by suitable coordination of mixing device, burner and / or combustion chamber achieved such that by fluctuations in the gas velocity Entropy waves generated at the location of the fuel injection Pressure fluctuations at the combustion chamber outlet induce which the pressure fluctuations in the combustion chamber are in phase opposition overlay and so overall a reduction in Cause fluctuation amplitudes. According to the invention this is through an appropriate choice of a number of parameters of the Combustion chamber, the mixing device and the combustion parameters achieved itself.
  • phase of these pressure fluctuations is relative to the phase of the acoustic pressure fluctuations of the Combustion chamber is characterized by a number of parameters of the combustion chamber, such as the length of the combustion chamber, the length of the mixing device and the temperatures of hot gas and fresh gas (and thus the sound velocities in hot and fresh gas) certainly.
  • This antiphase coordination is preferred by a corresponding one Choice of the length of the combustion chamber and / or the length reached the mixing section.
  • the setting can also be advantageous about the mass flow in the mixing device, such as a change of the compressor advance line setting, be.
  • the mass flow in the combustion chamber can also be advantageous or the hot gas temperature can be selected appropriately.
  • the exhaust housing is not shown the gas turbine with exhaust pipe and chimney, the compressor and collecting space of the turbine.
  • FIG. 1 shows a schematic diagram of a combustion chamber for premixed combustion 10.
  • the fuel is injected through the opening 14 (location A) and thus mixed with the combustion air.
  • the mixing device 12 is used to mix the combustion air and the fuel as homogeneously as possible.
  • the length of the mixing device 12 is L mix .
  • the mixing device is designed as a mixing tube.
  • the combustion takes place, as indicated by the flame 18 in FIG. 1.
  • the length of the combustion chamber 16 is L BK .
  • the burned air then flows into the turbine (not shown).
  • the fuel / air mixture in the mixing device 12, that is to say on the cold side of the flame 18, is referred to below as fresh gas; the combusted fuel / air mixture on the hot side of the flame 18 is referred to as hot gas.
  • the hydrodynamic component is due to fluctuations in the turbulent Mixing rate of fresh and hot gas attributed. This proportion does not lead to temperature fluctuations in the hot gas, since the amount of fresh gas and thus the amount of heat currently produced fluctuates, but not the fuel concentration in the fresh gas and thus the released Heat per mass.
  • the second, mixture-controlled component ⁇ Q ⁇ plays an important role in the undesired combustion chamber vibrations. This proportion is due to fluctuations in the speed at the location of the fuel injection. A fluctuation in the velocity ⁇ u I at the location of the fuel injection (location A) leads to a fluctuation in the heat release rate ⁇ Q ⁇ at location B after a certain delay time ⁇ mix , since such fluctuations vary the amount of air and thus the fuel concentration at location B.
  • the delay time ⁇ mix is essentially the residence time of the fuel / air mixture in the mixing device 12, and is therefore given by the length of the mixing device L mix and the flow rate of the fresh gas u c .
  • the additional phase shift of ⁇ is due to the fact that that the heat release rate at location B is proportional to the fuel / air ratio and therefore inversely proportional for speed fluctuation at location A.
  • acoustic fluctuations and vibrations in combustion chambers which are more or less pronounced depending on the particular design of a combustion chamber.
  • acoustic vibrations will be particularly pronounced, particularly close to the natural vibrations of the combustion chamber or a system of combustion chamber plus combustion chamber hood.
  • the boundary conditions of the acoustic vibrations result on the one hand from the fact that the combustion chamber outlet 20 has a high acoustic impedance, that is to say represents an acoustically hard end.
  • the boundary of the collecting space (not shown in FIG. 1) or a combustion chamber hood generally forms an acoustically hard end.
  • phase shift of ⁇ / 2 represents the usual phase shift between pressure and speed fluctuations in a standing acoustic wave.
  • the other two terms on the right side of equation (4) result from the transit time of a sound wave in the combustion chamber (speed of sound in the Hot gas c H ) and in the mixing device (speed of sound in the fresh gas c c ).
  • the available parameters are selected according to the invention such that the relative phase ⁇ rel at this frequency is an odd multiple of ⁇ . Then the entropy-wave-induced pressure disturbances and the pressure fluctuation of the standing acoustic wave at the combustion chamber outlet 20 overlap, so that the entire thermo-acoustic disturbance is minimized at this frequency.
  • the relative phase ⁇ rel at an frequency ⁇ is an even multiple of ⁇ , the entropy wave-induced pressure disturbances and the pressure fluctuation of the standing acoustic wave increase, which results in significantly higher vibration amplitudes and thus an increased mechanical load on the combustion chamber and the other associated disadvantages .
  • the design of the combustion chamber and premixing section is carried out in phase opposition by the choice of the length of the combustion chamber L BK and / or the length of the mixer L mix .
  • the large L BK and / or L mix are chosen so that the relative phase ⁇ rel , as defined in equation (5), becomes an odd multiple of ⁇ at the frequency to be damped.
  • the frequency to be damped will generally be a frequency at which the combustion chamber, due to its geometry and mechanical properties, tends to undergo strong pressure fluctuations.
  • the invention can also be carried out when the mixing section is very short or even completely eliminated or the mixing device is integrated into the fuel injection or the swirl generator (such as with the ABB double burner). It is important that the correspondingly shorter delay time ⁇ mix between the fuel injection and the location of the heat release is taken into account in the design.
  • FIGS. 2 and 3 The advantages of the invention are shown in a specific example in FIGS. 2 and 3.
  • the combustion chamber tends to have strong pressure fluctuations at a resonance frequency of approximately 128 Hz. This can also be seen from the solid lines in FIGS. 2 and 3, which were calculated using a numerical model for combustion chamber thermal acoustics.
  • FIG. 128 Hz This can also be seen from the solid lines in FIGS. 2 and 3, which were calculated using a numerical model for combustion chamber thermal acoustics.
  • FIG. 2 shows the pressure fluctuations with an in-phase superimposition of acoustic and entropy-wave-induced pressure fluctuations at 128 Hz
  • FIG. 3 shows the pressure fluctuations with an antiphase overlay according to the invention.
  • the amplitude of the pressure fluctuations at approximately 128 Hz can be considerably reduced by the design in opposite phase. Secondary peaks can occur, but overall the load on the combustion chamber due to thermoacoustic vibrations is significantly reduced.

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)
  • Separation By Low-Temperature Treatments (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Gas Burners (AREA)
EP97810491A 1997-07-15 1997-07-15 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz Expired - Lifetime EP0892219B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE59708564T DE59708564D1 (de) 1997-07-15 1997-07-15 Verfahren und Vorrichtung zum Minimieren thermoakustischer Schwingungen in Gasturbinenbrennkammern
EP97810491A EP0892219B1 (fr) 1997-07-15 1997-07-15 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz
AT97810491T ATE226708T1 (de) 1997-07-15 1997-07-15 Verfahren und vorrichtung zum minimieren thermoakustischer schwingungen in gasturbinenbrennkammern
US09/111,869 US6170265B1 (en) 1997-07-15 1998-07-08 Method and device for minimizing thermoacoustic vibrations in gas-turbine combustion chambers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810491A EP0892219B1 (fr) 1997-07-15 1997-07-15 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz

Publications (2)

Publication Number Publication Date
EP0892219A1 true EP0892219A1 (fr) 1999-01-20
EP0892219B1 EP0892219B1 (fr) 2002-10-23

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EP97810491A Expired - Lifetime EP0892219B1 (fr) 1997-07-15 1997-07-15 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz

Country Status (4)

Country Link
US (1) US6170265B1 (fr)
EP (1) EP0892219B1 (fr)
AT (1) ATE226708T1 (fr)
DE (1) DE59708564D1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2348484A (en) * 1997-03-10 2000-10-04 Gen Electric Premixer for a combustion chamber
WO2002025174A1 (fr) * 2000-09-21 2002-03-28 Siemens Westinghouse Power Corporation Resonateurs modulaires permettant de supprimer les instabilites de combustion dans des centrales electriques de turbine a gaz
DE102005035085A1 (de) * 2005-07-20 2007-02-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Einstellung der akustischen Eigenschaften einer Brennkammer
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
CN113970445A (zh) * 2021-10-14 2022-01-25 上海交通大学 熵-声试验平台及其试验方法

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6879922B2 (en) * 2001-09-19 2005-04-12 General Electric Company Systems and methods for suppressing pressure waves using corrective signal
US7234304B2 (en) 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
DE10257244A1 (de) * 2002-12-07 2004-07-15 Alstom Technology Ltd Verfahren und Vorrichtung zur Beeinflussung thermoakustischer Schwingungen in Verbrennungssystemen
DE10257245A1 (de) * 2002-12-07 2004-07-15 Alstom Technology Ltd Verfahren und Vorrichtung zur Beeinflussung thermoakustischer Schwingungen in Verbrennungssystemen
US8028512B2 (en) 2007-11-28 2011-10-04 Solar Turbines Inc. Active combustion control for a turbine engine
CN118602397B (zh) * 2024-06-13 2025-12-30 东南大学 一种利用声波稳燃的方法、装置及煤粉燃烧器

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3951566A (en) * 1973-12-11 1976-04-20 Electricite De France (Service National) Axial-flow fan with by-pass pipe or pipes
US4199295A (en) * 1976-11-05 1980-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Method and device for reducing the noise of turbo-machines
US5092425A (en) * 1990-04-02 1992-03-03 The United States Of America As Represented By The Secretary Of The Air Force Jet noise suppressor and method

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4122674A (en) * 1976-12-27 1978-10-31 The Boeing Company Apparatus for suppressing combustion noise within gas turbine engines
US4409787A (en) * 1979-04-30 1983-10-18 General Electric Company Acoustically tuned combustor
US4760695A (en) * 1986-08-28 1988-08-02 United Technologies Corporation Acoustic oscillatory pressure control for ramjet
EP0576717A1 (fr) 1992-07-03 1994-01-05 Abb Research Ltd. Chambre de combustion de turbine à gaz
US5428951A (en) * 1993-08-16 1995-07-04 Wilson; Kenneth Method and apparatus for active control of combustion devices
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3951566A (en) * 1973-12-11 1976-04-20 Electricite De France (Service National) Axial-flow fan with by-pass pipe or pipes
US4199295A (en) * 1976-11-05 1980-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Method and device for reducing the noise of turbo-machines
US5092425A (en) * 1990-04-02 1992-03-03 The United States Of America As Represented By The Secretary Of The Air Force Jet noise suppressor and method

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2348484A (en) * 1997-03-10 2000-10-04 Gen Electric Premixer for a combustion chamber
GB2348484B (en) * 1997-03-10 2001-03-21 Gen Electric Dynamically uncoupled low NOx combuster
WO2002025174A1 (fr) * 2000-09-21 2002-03-28 Siemens Westinghouse Power Corporation Resonateurs modulaires permettant de supprimer les instabilites de combustion dans des centrales electriques de turbine a gaz
US7194862B2 (en) 2000-09-21 2007-03-27 Siemens Power Generation, Inc. Resonator adopting counter-bored holes and method of suppressing combustion instabilities
US7549506B2 (en) 2000-09-21 2009-06-23 Siemens Energy, Inc. Method of suppressing combustion instabilities using a resonator adopting counter-bored holes
DE102005035085A1 (de) * 2005-07-20 2007-02-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Einstellung der akustischen Eigenschaften einer Brennkammer
DE102005035085B4 (de) * 2005-07-20 2014-01-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Einstellung der akustischen Eigenschaften einer Brennkammer
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
US11421884B2 (en) 2011-12-13 2022-08-23 General Electric Company System for aerodynamically enhanced premixer for reduced emissions
US11421885B2 (en) 2011-12-13 2022-08-23 General Electric Company System for aerodynamically enhanced premixer for reduced emissions
CN113970445A (zh) * 2021-10-14 2022-01-25 上海交通大学 熵-声试验平台及其试验方法
CN113970445B (zh) * 2021-10-14 2023-02-10 上海交通大学 熵-声试验平台及其试验方法

Also Published As

Publication number Publication date
US6170265B1 (en) 2001-01-09
DE59708564D1 (de) 2002-11-28
ATE226708T1 (de) 2002-11-15
EP0892219B1 (fr) 2002-10-23

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