EP0974788B1 - Dispositif d'atténuation adaptée de bruit dans une turbomachine - Google Patents

Dispositif d'atténuation adaptée de bruit dans une turbomachine Download PDF

Info

Publication number
EP0974788B1
EP0974788B1 EP98810714.0A EP98810714A EP0974788B1 EP 0974788 B1 EP0974788 B1 EP 0974788B1 EP 98810714 A EP98810714 A EP 98810714A EP 0974788 B1 EP0974788 B1 EP 0974788B1
Authority
EP
European Patent Office
Prior art keywords
liquid
combustion chamber
flow
helmholtz resonator
turbomachine
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.)
Expired - Lifetime
Application number
EP98810714.0A
Other languages
German (de)
English (en)
Other versions
EP0974788A1 (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 Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP98810714.0A priority Critical patent/EP0974788B1/fr
Publication of EP0974788A1 publication Critical patent/EP0974788A1/fr
Application granted granted Critical
Publication of EP0974788B1 publication Critical patent/EP0974788B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • 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 device for targeted sound attenuation within a turbomachine with a combustion chamber according to the preamble of claim 1.
  • a device for targeted sound attenuation within a turbomachine with a combustion chamber according to the preamble of claim 1.
  • Such a device is known from document GB-A-2 288 660 already known.
  • Oscillations occurring in the flow flow of gas turbines are not only capable of sustainably influencing the combustion process of the air-gas mixture, but also transmit the pressure waves propagating in the gaseous medium Moreover, on the, the flow paths immediately surrounding housing parts of the gas turbine plant, in addition to temperature and pressure loads due to the mechanical oscillating vibrations another, significant criterion for material fatigue, which not least the life of a gas turbine plant is decisively influenced.
  • Helmholtz resonators As sound-damping elements Helmholtz resonators have become known, which are used within the flow of gas turbine systems. The use of Helmholtz resonators in gas turbines is in an article by JJ Keller and E. Zauner, "On the Use of Helmholtz Resonators as Sound Attentuators", Z. on Math. Phys., 46 (1995), pages 297 to 326 , described. Helmholtz resonators are characterized in particular by the fact that they have a so-called Helmholtz resonator volume through which the flow flow passes.
  • the Helmholtz resonator volume also has at least one Strömungseinlledge- and a -auslwiekanal, the flow channel diameter are dimensioned smaller than the flow cross-section within the Helmholtz resonator volume.
  • the flow-through sequence of flow channel sections having different flow diameters imposes on the flow a resonant oscillation resulting from the periodic conversion of potential energy within compressed flow volume ranges to kinetic energy.
  • Helmholtz resonators Although using Helmholtz resonators significant vibration damping can be made in the respective flow systems, but provide the known Helmholtz resonator systems due to their unique fixed size and design limited opportunities individual frequency adjustments to set a desired low resonant frequency, typically less than 100 Hz make , The use of Helmholtz resonators for targeted sound attenuation in gas turbine systems often leads to very large volume areas in order to achieve desired resonance frequencies less than 100 Hz can.
  • the font GB-A-22 288,660 discloses a device for damping thermo-acoustic vibrations in a combustion chamber of a gas turbine.
  • the device comprises a Helmholtz resonator with a resonator chamber and a connecting tube, through which the resonator chamber communicates with the combustion chamber.
  • a constant damping power is achieved even under changing operating conditions in that the Helmholtz resonator is equipped with means for controlling the resonator frequency as a function of the frequency of the combustion chamber vibrations.
  • the invention has the object of providing a device for targeted sound attenuation within a turbomachine with a combustion chamber according to the preamble of claim 1 using a Helmholtz resonator such that the measures for noise reduction for the avoidance of thermoacoustic oscillations within the flow with the simplest possible Means can be further improved. Furthermore, these measures should be associated with the least possible investment. In particular, the sound attenuation should offer extended possibilities to make desirable resonant frequency shifts of the damper elements in a large range to small frequencies out, and also to reduce the size of the Helmholtz resonators as possible.
  • the inventive concept for sound damping within a turbomachine with a combustion chamber provides an injection nozzle within the Helmholtz resonator volume before entering the flow channel, which connects the Helmholtz resonator volume with the combustion chamber.
  • the injection nozzle arrangement becomes liquid, preferably Water, atomized in the direction of the flow channel towards the combustion chamber in the finest liquid droplets, so that forms a liquid-air mixture before entering the combustion chamber.
  • This device is based on the idea to change the speed of sound within the flow channel by targeted introduction of a liquid-air mixture, so as to selectively influence the resonance behavior of the entire sound system.
  • the injection nozzle arrangement is designed such that the liquid droplet size and the degree of atomization can be regulated in the desired manner by appropriate nozzle variation.
  • the injector arrangement which can be set in a wide range, makes it possible to influence the sound propagation behavior within the flow channel by specific introduction of an additional mass flow in the form of liquid droplets and to adapt it individually to the existing flow geometries, so that the occurrence of thermoacoustic oscillations can be effectively counteracted. This makes it possible to tune the muffler to very low vibration frequencies.
  • Another advantage associated with the targeted introduction of a liquid-gas mixture within the Helmholtz resonator volume relates to the protection of the Helmholtz resonator from overheating resulting from the heat radiation from the combustion chamber through the flow channel in the direction of the Helmholtz Resonator volume could result.
  • the previous use of Helmholtz resonators requires that a certain minimum flow rate of cooling air through the Helmholtz resonator predominates.
  • no additional air flow is required for cooling purposes.
  • FIG. 1 shows a sound damping device for a turbomachine, for example, a gas turbine plant with a combustion chamber 1, in which via a flow channel 2 pre-compressed air is introduced with the addition of fuel.
  • a turbomachine for example, a gas turbine plant with a combustion chamber 1
  • a flow channel 2 pre-compressed air is introduced with the addition of fuel.
  • the representation according to FIG. 1 For reasons of clarity, this does not mean that the fuel supply is relevant.
  • thermoacoustic vibrations occur within the combustion chamber, which it applies with in the FIG. 1 to dampen the device shown.
  • a Helmholtz resonator volume 3 is provided, which has an air supply line 4.
  • the Helmholtz resonator volume 3 alone is only able to exert a certain limited damping effect on the thermoacoustic oscillations forming inside the combustion chamber 1, it is only through the provision of an injection nozzle arrangement 5 within the Helmholtz Resonator volume 3 possible to adjust the sound damping effect individually on the forming within the combustion chamber thermoacoustic oscillations.
  • an injection nozzle arrangement 5 which is arranged in front of the flow channel 2 in the flow direction of the inlet air entering the combustion chamber, a liquid, preferably water atomized into the finest liquid droplets, so that within the Flow channel 2 forms a liquid-air mixture 5 ', which preferably fills the entire flow channel 2.
  • the injection nozzle assembly 5 is preferably arranged concentrically within the air supply line 4, so that a sufficient amount of supply air (see arrows) is introduced into the interior of the Helmholtz resonator 3.
  • a sufficient amount of supply air see arrows
  • the mass flow of the atomized liquid droplets and the atomization degree of the liquid supplied by the injection nozzle 5 changes the prevailing within the liquid-gas mixture sound velocity, whereby a targeted influence on the resonance behavior of the Helmholtz resonator volume 3 can be taken.
  • the speed of sound decreases significantly.
  • the mass flow of the atomized liquid is to regulate individually.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (6)

  1. Dispositif d'atténuation contrôlée du bruit produit à l'intérieur d'une machine à écoulement dotée d'une chambre de combustion (1) dans laquelle un fluide compressible, de préférence de l'air, est apporté par un canal d'écoulement (2) et dans laquelle le fluide compressible peut être allumé par addition de combustible, et présentant un volume (3) de résonateur de Helmholtz relié au canal d'écoulement (2) en amont de son entrée dans la chambre de combustion (1) dans la direction d'écoulement,
    caractérisé en ce que
    avant l'entrée dans le canal d'écoulement (2), un ensemble (5) de tuyère d'injection par lequel le liquide peut être pulvérisé en direction du canal d'écoulement (2) en très fines gouttes de liquide sous la forme d'un mélange (5') de liquide et d'air est prévu à l'intérieur du volume (3) de résonateur de Helmholtz.
  2. Dispositif selon la revendication 1, caractérisé en ce que le débit massique de liquide ainsi que le degré de pulvérisation peuvent être régulés activement.
  3. Dispositif selon les revendications 1 ou 2, caractérisé en ce que l'ensemble (5) de tuyère d'injection présente une tuyère de pulvérisation qui forme des gouttes de liquide d'un diamètre moyen d'environ 20 µm.
  4. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce que l'ensemble (5) de tuyère d'injection est dimensionné et disposé de telle sorte que le canal d'écoulement (2) soit complètement rempli du mélange (5') de liquide et d'air.
  5. Dispositif selon l'une des revendications 1 à 4, caractérisé en ce que le volume (3) de résonateur de Helmholtz présente une partie d'admission d'air et une partie de sortie d'air, le diamètre de la partie de sortie d'air étant supérieur au diamètre de la partie d'entrée d'air et en ce que le canal d'écoulement (2) est situé entre la partie de sortie d'air et la chambre de combustion (1).
  6. Machine d'écoulement présentant un dispositif selon l'une des revendications 1 à 5, caractérisée en ce que la machine d'écoulement est une turbine à gaz.
EP98810714.0A 1998-07-23 1998-07-23 Dispositif d'atténuation adaptée de bruit dans une turbomachine Expired - Lifetime EP0974788B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP98810714.0A EP0974788B1 (fr) 1998-07-23 1998-07-23 Dispositif d'atténuation adaptée de bruit dans une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810714.0A EP0974788B1 (fr) 1998-07-23 1998-07-23 Dispositif d'atténuation adaptée de bruit dans une turbomachine

Publications (2)

Publication Number Publication Date
EP0974788A1 EP0974788A1 (fr) 2000-01-26
EP0974788B1 true EP0974788B1 (fr) 2014-11-26

Family

ID=8236211

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810714.0A Expired - Lifetime EP0974788B1 (fr) 1998-07-23 1998-07-23 Dispositif d'atténuation adaptée de bruit dans une turbomachine

Country Status (1)

Country Link
EP (1) EP0974788B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2569786C2 (ru) * 2010-04-13 2015-11-27 Сименс Акциенгезелльшафт Устройство резонатора для демпфирования колебаний давления в камере сгорания и способ для управления системой сгорания

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19851636A1 (de) * 1998-11-10 2000-05-11 Asea Brown Boveri Dämpfungsvorrichtung zur Reduzierung der Schwingungsamplitude akustischer Wellen für einen Brenner
DE10026121A1 (de) * 2000-05-26 2001-11-29 Alstom Power Nv Vorrichtung zur Dämpfung akustischer Schwingungen in einer Brennkammer
EP1213538B1 (fr) 2000-12-08 2006-09-06 Alstom Technology Ltd Dispositif pour gaz d'échappement comprenant un résonateur de Helmholtz
GB2396687A (en) * 2002-12-23 2004-06-30 Rolls Royce Plc Helmholtz resonator for combustion chamber use
EP1557609B1 (fr) 2004-01-21 2016-03-16 Siemens Aktiengesellschaft Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion
EP1762786A1 (fr) * 2005-09-13 2007-03-14 Siemens Aktiengesellschaft Procédé et appareil pour réduire les vibrations thermo-accoustiques, en particulier dans une turbine
US20100236245A1 (en) * 2009-03-19 2010-09-23 Johnson Clifford E Gas Turbine Combustion System
US8789372B2 (en) 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator
EP2397761B1 (fr) 2010-06-16 2021-10-06 Ansaldo Energia Switzerland AG Amortisseur de Helmholtz
EP2397759A1 (fr) * 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur
EP2474784A1 (fr) 2011-01-07 2012-07-11 Siemens Aktiengesellschaft Système de combustion pour turbine à gaz comprenant un résonateur
US9341375B2 (en) 2011-07-22 2016-05-17 General Electric Company System for damping oscillations in a turbine combustor
US8966903B2 (en) 2011-08-17 2015-03-03 General Electric Company Combustor resonator with non-uniform resonator passages
CN103032898A (zh) * 2012-12-31 2013-04-10 中国人民解放军国防科学技术大学 一种燃烧室混合增强装置

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59208193D1 (de) * 1992-07-03 1997-04-17 Abb Research Ltd Nachbrenner
DE4305333C1 (de) * 1993-02-20 1994-07-07 Fasag Ag Suhr Geräuschdämpfungsvorrichtung zur Reduktion von Mündungsgeräuschen bei Anlagen mit pulsierenden Gasströmungen
DE4414232A1 (de) * 1994-04-23 1995-10-26 Abb Management Ag Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2569786C2 (ru) * 2010-04-13 2015-11-27 Сименс Акциенгезелльшафт Устройство резонатора для демпфирования колебаний давления в камере сгорания и способ для управления системой сгорания

Also Published As

Publication number Publication date
EP0974788A1 (fr) 2000-01-26

Similar Documents

Publication Publication Date Title
EP0974788B1 (fr) Dispositif d'atténuation adaptée de bruit dans une turbomachine
EP0985882B1 (fr) Amortissement des vibrations dans des combusteurs
DE10205839B4 (de) Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
DE19640980B4 (de) Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
EP1004823B1 (fr) Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur
EP1423645B1 (fr) Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
DE102010000254B4 (de) Landgestütztes Einfachzyklus-Hybridtriebwerk auf der Basis eines Pulsdetonationsbrenners zur Energieerzeugung
EP1481195B1 (fr) Bruleur, procede de fonctionnement d'un bruleur et turbine a gaz
DE10325691A1 (de) Wiederaufheizverbrennungssystem für eine Gasturbine
EP1483536B1 (fr) Turbine a gaz
EP2167796B1 (fr) Dispositif et procédé d'amélioration de l'atténuation d'ondes acoustiques
DE10040869A1 (de) Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
WO1993010401A1 (fr) Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP1762786A1 (fr) Procédé et appareil pour réduire les vibrations thermo-accoustiques, en particulier dans une turbine
EP0971172B1 (fr) Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
EP0576717A1 (fr) Chambre de combustion de turbine à gaz
DE102008016931A1 (de) System zur Reduktion der Brennkammerdynamik
DE19948674B4 (de) Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen
EP1010939B1 (fr) Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement
DE102004010620B4 (de) Brennkammer zur wirksamen Nutzung von Kühlluft zur akustischen Dämpfung von Brennkammerpulsation
WO2010149420A1 (fr) Agencement de chambre de combustion pour l'amortissement de vibrations thermo-acoustiques, turbine à gaz et procédé pour utiliser une telle turbine à gaz
EP0892219B1 (fr) Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz
EP1775515A2 (fr) Dispositif résonant pour chambre de combustion, chambre de combustion et procédé pour ajuster les caractéristiques acoustiques d'une chambre de combustion
EP1182399A2 (fr) Procédé pour la réduction des oscillations thermoacoustiques dans une turbomachine en utilisant le dispositif de combustion
EP1114967B1 (fr) Procédé et dispositif pour supprimer les tourbillons dans une chambre à combustion d'une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20000510

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ABB ALSTOM POWER (SCHWEIZ) AG

AKX Designation fees paid

Free format text: DE GB

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM (SWITZERLAND) LTD

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM TECHNOLOGY LTD

17Q First examination report despatched

Effective date: 20130917

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 59814553

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F23M0013000000

Ipc: F23R0003020000

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/02 20060101AFI20140618BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20140819

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 59814553

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ABB (SCHWEIZ) AG, BADEN, AARGAU, CH

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 59814553

Country of ref document: DE

Effective date: 20141231

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 59814553

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20150721

Year of fee payment: 18

Ref country code: GB

Payment date: 20150721

Year of fee payment: 18

26N No opposition filed

Effective date: 20150827

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 59814553

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 59814553

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160723

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160723