EP1010939A1 - Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement - Google Patents

Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement Download PDF

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Publication number
EP1010939A1
EP1010939A1 EP98811230A EP98811230A EP1010939A1 EP 1010939 A1 EP1010939 A1 EP 1010939A1 EP 98811230 A EP98811230 A EP 98811230A EP 98811230 A EP98811230 A EP 98811230A EP 1010939 A1 EP1010939 A1 EP 1010939A1
Authority
EP
European Patent Office
Prior art keywords
fuel
fuel supply
supply system
volume
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
Application number
EP98811230A
Other languages
German (de)
English (en)
Other versions
EP1010939B1 (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.)
General Electric Switzerland GmbH
Original Assignee
ABB Alstom Power Switzerland Ltd
Alstom Power Schweiz 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 ABB Alstom Power Switzerland Ltd, Alstom Power Schweiz AG filed Critical ABB Alstom Power Switzerland Ltd
Priority to EP98811230A priority Critical patent/EP1010939B1/fr
Priority to DE59810760T priority patent/DE59810760D1/de
Priority to US09/458,095 priority patent/US6305927B1/en
Publication of EP1010939A1 publication Critical patent/EP1010939A1/fr
Application granted granted Critical
Publication of EP1010939B1 publication Critical patent/EP1010939B1/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
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement
    • 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 present invention relates to the field of burners, in particular the burner for use in gas turbines. It concerns a burner with a fuel supply system, in which the fuel supply system is fuel transported to the burner, the fuel in the burner into a combustion chamber is injected where the fuel is burned.
  • Burners of gas turbines serve the fuel and the combustion air in a controlled manner and controllably inject into a combustion chamber and there to burn the fuel.
  • the burners can be used in many different ways Arrangement in the wall of the combustion chamber, and will be charged with fuel by means of a fuel supply system.
  • the injection The fuel in the burner must be in order to optimally control the combustion process in the various operating states of the turbine ensure controllable and done in the best possible way.
  • More and more strict regulations regarding emissions of combustion processes make a highly specialized and complicated injection and mixing of combustion air and fuel in the Burner essential.
  • EP-B1-0 321 809 describes a so-called double-cone burner become known for liquid and gaseous fuels without a premix section, in which combustion air supplied from outside through at least two inlet slots tangentially between displaced, hollow half-cones enters and flows there towards the combustion chamber, and in which on the Combustion chamber facing away, tapered side of the half-cones fuel centrally or from distribution channels that run along the air inlet slots Rows of holes are injected transversely into the incoming air.
  • acoustic oscillations which also under the term "singing flame” are known. These are mostly oscillations, which results from the interaction of inflows of the combustion mixture and the actual combustion process in the combustion chamber.
  • These largely coherently periodic pressure fluctuations can, for example with a burner of the type mentioned above under typical operating conditions to acoustic vibrations with frequencies of about 80 to 100 Hz to lead. Since these frequencies have typical fundamental eigenmodes of Combustion chambers of gas turbines can collapse, make them thermoacoustic Oscillations are a problem.
  • the invention is therefore based on the object, a burner with at least a fuel supply system through which a fuel flow to the burner is supplied, the supplied fuel is injected via fuel nozzles, and then burned in a combustion chamber provide who is able to train and reinforce periodic To prevent pressure fluctuations in the combustion chamber at least partially.
  • a first preferred embodiment of the invention is characterized in that that the means at least a first, immediately upstream of the fuel nozzles arranged volume include, through which volume the fuel flow flows, and that this first volume is upstream over a first Narrowing with the fuel delivery system located further upstream communicates.
  • This first volume is essentially preferred chosen smaller than a certain critical volume, and especially continues the cross-sectional area of the first narrowing is less than a certain critical Cross-sectional area formed.
  • Another embodiment of the invention is characterized in that a second volume is arranged upstream of the first constriction which the fuel flow flows, and that this second volume upstream via a second constriction with the one located further upstream Fuel supply system is connected.
  • This arrangement allows the effective prevention of coupling under special, essentially unchangeable Design specifications of the burner and the fuel supply system.
  • the fuel supply system can be viewed acoustically as shown in FIG. 1 as a throttle, ie as an opening 10 with a negligible length and cross-sectional area A F , through which fuel the density ⁇ F from a large volume at pressure p F to another large one Volume, the combustion chamber 11, flows at pressure p I. It is assumed that the following applies: p F > p I. In addition, it is assumed that the fuel supply volume has a constant pressure p F , while the pressure in the injection space p I can be subject to fluctuations.
  • the pressure fluctuations in the injection space therefore have a directly linear effect to fluctuations in fuel injection speed 12 and vice versa, i.e. there is a direct coupling of the two sizes.
  • instabilities arise in the system consisting of the fuel supply system, Burner and combustion chamber on once the fuel injection speed 12 falls below a value of approximately 125 m / s.
  • One way to achieve arbitrarily small values for ⁇ at any oscillation frequency is, for example, the use of check valves with a second, upstream opening of variable cross-sectional area. In this case, even for very small ones Fuel injection speeds of pressure drop across the fuel supply system are kept to a minimum.
  • a fuel nozzle of cross-sectional area AF with an upstream fuel supply line of length L and cross-sectional area AT forms an acoustic coupling of the shape leads, where c F represents the speed of sound in the fuel gas.
  • each volume between the fuel line 15 and the fuel nozzle 10 must be small compared to a critical volume V CRIT , which is given by:
  • FIG. 3 schematically shows a burner of the applicant's type EV17i, such as is installed in a gas turbine of the applicant's type GT26.
  • the fuel is supplied to the burner 14 via a fuel supply line 15.
  • the line 15 initially opens into an annular distribution space 16, from which fuel distribution channels run along the conical outer surface of the double-cone burner.
  • these distribution channels On the side facing the burner, these distribution channels have a plurality of fuel nozzles 10, through which the fuel can flow into the burner and thus into the combustion chamber 11.
  • the diameter of the fuel feed 15 is approximately 38 mm, although it should not be more than 21 mm according to the above criterion.
  • a simple way of acoustically hardening the specified structure is the introduction of a Helmholtz volume with a suitable cross-sectional area e A and length L between the fuel supply line 15 and the fuel nozzles 10, as is shown schematically in FIG. 2b). It is of great advantage to set the dimensioning of the volume and the constriction in such a way that at least one resonance of the fuel supply system coincides with the most important fundamental acoustic natural frequency of the combustion chamber.
  • the response function ⁇ ( ⁇ ) can be calculated.
  • the damping factor ⁇ ( ⁇ ) (attenuation factor) as a function of the frequency of the pressure fluctuations under consideration for the conditions listed in Table 1 is shown in FIG.
  • FIG. 4 shows that the damping only occurs in narrow areas around the resonance frequencies of the fuel supply system. It can also be clearly seen from FIG.
  • the fuel supply system behaves like a simple and almost completely undamped throttle, and thus the resonance behavior of the fuel supply system does not at all match that of the combustion chamber is coordinated.
  • a line constriction 17 as also shown in FIG. 3, is introduced into the fuel supply line 15, the resonance frequency of the fuel supply system shifts and widens in the range from 90 to 100 Hz and the minimum value of ⁇ at this frequency is approximately 0.35-0.4.
  • This is done with a simple use of a slide-in device 17 (or a constriction caused in another way) of 300 mm in length and an inner diameter of 21 mm.
  • a further improvement can be achieved with the values given in table 2 by increasing the length of the insert 17 from 300 mm to 500 mm and additionally reducing the first volume from 650 cm 3 to 400 cm 3 .
  • the absorption profile for the values from Table 2 is shown in FIG. 5. Essentially The minimum value changes as a result of these further measures from ⁇ at the frequency of 90 to 100Hz to a value of 0.2, which is a doubling corresponds to the absorption efficiency in comparison to the first example.
  • the resulting absorption profile is shown in FIG. 6, it shows in the resonance range from 90 to 100Hz an absorption of remarkable 90% in Compared to the simple throttle.
  • the acoustic hardening of a burner of the type EV18 from the applicant, as is installed in a gas turbine of the type GT26, is to be used.
  • the fuel is supplied to the burner 14 via annular fuel distribution lines 18, which jointly supply the burners arranged in a ring in the annular combustion chamber of the turbine.
  • the fuel branches off from the annular fuel distribution line 18 via a second constriction 19 and enters a volume which is normally formed by the volumes 20 and 22 without the partition 23 shown in FIG. 8 and the first constriction 21.
  • the fuel is guided through the fuel distribution channels 22 along the cone of the burner 14 and passes through the fuel nozzles 10 into the combustion chamber 11, where it is mixed with combustion air.
  • a solution to acoustic hardening must now be found here, in which the fuel distribution system has to be changed as little as possible.
  • the easiest way to do this is to arrange two volumes upstream of the fuel nozzle 10 and connected to the fuel supply line via two constrictions, as is shown schematically in FIG.
  • a possible technical implementation is shown in Figure 8.
  • a partition 23 separates the large volume into the fuel distribution channels 22 and a second volume 20, and a constriction 21, which is wound around the burner and is designed as a line, connects the two volumes.
  • the absorption characteristic in FIG. 9 is obtained.
  • Size unit value print bar 18th Cross-sectional area of the nozzle m 2 9.08e-5 Temperature of methane K 323 Mass flow of methane kg / s 0.133 Length of the second narrowing m 0.04 Cross-sectional area of the second constriction m 2 0.000314 Second volume m 3 0.0015 Length of the first narrowing m 1.2 Cross-sectional area of the first constriction m 2 0.000314 First volume m 3 0.00015
  • this arrangement and dimensioning are used of two volumes connected in series a perfect damping of the acoustic coupling with the natural frequency of the combustion chamber of approx. 90 Hz a considerable width of the resonance condition, with a deviation of approx. ⁇ 30Hz namely 2/3 are still absorbed by the resonance condition.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP98811230A 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement Expired - Lifetime EP1010939B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP98811230A EP1010939B1 (fr) 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement
DE59810760T DE59810760D1 (de) 1998-12-15 1998-12-15 Brennkammer mit akustisch gedämpftem Brennstoffversorgungssystem
US09/458,095 US6305927B1 (en) 1998-12-15 1999-12-10 Burner with acoustically damped fuel supply system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811230A EP1010939B1 (fr) 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement

Publications (2)

Publication Number Publication Date
EP1010939A1 true EP1010939A1 (fr) 2000-06-21
EP1010939B1 EP1010939B1 (fr) 2004-02-11

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EP98811230A Expired - Lifetime EP1010939B1 (fr) 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement

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US (1) US6305927B1 (fr)
EP (1) EP1010939B1 (fr)
DE (1) DE59810760D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2397760A1 (fr) * 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur et procédé pour le concevoir
US8474265B2 (en) 2009-07-29 2013-07-02 General Electric Company Fuel nozzle for a turbine combustor, and methods of forming same

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1342952A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement d'un brûleur et turbine à gaz
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
US6820431B2 (en) * 2002-10-31 2004-11-23 General Electric Company Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly
WO2004051063A1 (fr) * 2002-12-02 2004-06-17 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
US8028512B2 (en) 2007-11-28 2011-10-04 Solar Turbines Inc. Active combustion control for a turbine engine
JP5357631B2 (ja) * 2009-06-09 2013-12-04 三菱重工業株式会社 燃料ノズル、これを備えた燃焼器及びガスタービン
US8322140B2 (en) * 2010-01-04 2012-12-04 General Electric Company Fuel system acoustic feature to mitigate combustion dynamics for multi-nozzle dry low NOx combustion system and method
US9127837B2 (en) * 2010-06-22 2015-09-08 Carrier Corporation Low pressure drop, low NOx, induced draft gas heaters
US9188340B2 (en) * 2011-11-18 2015-11-17 General Electric Company Gas turbine combustor endcover with adjustable flow restrictor and related method
US9400108B2 (en) 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
DE102019110258A1 (de) 2019-04-15 2020-10-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Injektorvorrichtung für eine Triebwerksvorrichtung, Triebwerksvorrichtung und Luft- und/oder Raumfahrzeug

Citations (2)

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Publication number Priority date Publication date Assignee Title
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
WO1993010401A1 (fr) * 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz

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US1702731A (en) * 1929-02-19 Method of and apparatus for combustion otf
US804002A (en) * 1903-10-10 1905-11-07 Eugene Alfred Javal Gas-blowpipe.
US2765004A (en) * 1953-07-21 1956-10-02 Harold W Williams Dropper assembly
US2943641A (en) * 1956-01-30 1960-07-05 Richfield Oil Corp Device for attenuating pulsative flow in gases
US3807527A (en) * 1973-03-14 1974-04-30 Tenneco Inc Pulse converter for exhaust system
US4464314A (en) * 1980-01-02 1984-08-07 Surovikin Vitaly F Aerodynamic apparatus for mixing components of a fuel mixture
JPS57108512A (en) * 1980-12-26 1982-07-06 Babcock Hitachi Kk Gas burner
US4760695A (en) * 1986-08-28 1988-08-02 United Technologies Corporation Acoustic oscillatory pressure control for ramjet
US5349813A (en) * 1992-11-09 1994-09-27 Foster Wheeler Energy Corporation Vibration of systems comprised of hot and cold components
US5494438A (en) * 1994-02-08 1996-02-27 National Science Council Sudden expansion combustion chamber with slotted inlet port
IT1278601B1 (it) * 1994-07-05 1997-11-24 Necchi Compressori Silenziatore per motocompressore, per apparati frigoriferi
DE19504610C2 (de) * 1995-02-13 2003-06-18 Alstom Vorrichtung zur Dämpfung thermoakustischer Druckschwingungen
DE19542918A1 (de) * 1995-11-17 1997-05-22 Asea Brown Boveri Vorrichtung zur Dämpfung thermoakustischer Druckschwingungen
US6058709A (en) * 1996-11-06 2000-05-09 The United States Of America Represented By The United States Department Of Energy Dynamically balanced fuel nozzle and method of operation
DE19649486A1 (de) * 1996-11-29 1998-06-04 Abb Research Ltd Brennkammer

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
WO1993010401A1 (fr) * 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8474265B2 (en) 2009-07-29 2013-07-02 General Electric Company Fuel nozzle for a turbine combustor, and methods of forming same
EP2397760A1 (fr) * 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur et procédé pour le concevoir
US8931589B2 (en) 2010-06-16 2015-01-13 Alstom Technology Ltd. Damper arrangement and method for designing same

Also Published As

Publication number Publication date
EP1010939B1 (fr) 2004-02-11
DE59810760D1 (de) 2004-03-18
US6305927B1 (en) 2001-10-23

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