EP2500648B1 - Chambre de combustion de turbines à gaz - Google Patents

Chambre de combustion de turbines à gaz Download PDF

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Publication number
EP2500648B1
EP2500648B1 EP11158268.0A EP11158268A EP2500648B1 EP 2500648 B1 EP2500648 B1 EP 2500648B1 EP 11158268 A EP11158268 A EP 11158268A EP 2500648 B1 EP2500648 B1 EP 2500648B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
gas turbine
resonance chambers
corrugated component
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.)
Not-in-force
Application number
EP11158268.0A
Other languages
German (de)
English (en)
Other versions
EP2500648A1 (fr
Inventor
Andreas Böttcher
Olga Deiss
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 ES11158268T priority Critical patent/ES2427440T3/es
Priority to EP11158268.0A priority patent/EP2500648B1/fr
Priority to US13/414,051 priority patent/US8464536B2/en
Priority to RU2012109927/06A priority patent/RU2012109927A/ru
Priority to CN201210069388.1A priority patent/CN102679396B/zh
Publication of EP2500648A1 publication Critical patent/EP2500648A1/fr
Application granted granted Critical
Publication of EP2500648B1 publication Critical patent/EP2500648B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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 invention relates to a gas turbine combustion chamber, with a combustion chamber interior and a combustion chamber wall, which has a substantially rotationally symmetrical cross section.
  • a gas turbine plant comprises in the simplest case a compressor, a combustion chamber and a turbine.
  • the compressor there is a compression of sucked air, which is then admixed with a fuel.
  • the combustion chamber the mixture is combusted, the combustion exhaust gases being supplied to the turbine, from which energy is withdrawn from the combustion exhaust gases and converted into mechanical energy.
  • thermoacoustic oscillations in the combustors of gas turbines - or turbomachines in general - represent a problem in the design and operation of new combustors, combustor parts and burners for such turbomachines.
  • thermoacoustic vibrations can increase. This can lead to an oscillating interaction between thermal and acoustic disturbances, which can cause high loads on the combustion chamber and rising emissions.
  • thermoacoustic oscillations are therefore in the prior art, for example, Helmholtz resonators for Damping used to dampen the amplitude of vibrations of certain frequencies.
  • Helmholtz resonators attenuate depending on the cross-sectional area of the connecting tube and the resonator volume, in particular the amplitude of vibrations, with the Helmholtz frequency.
  • These Helmholtz resonators are mostly small boxes, which are individually welded onto the combustion chamber wall of the gas turbine. However, this is very complicated and expensive. In addition, these small boxes and their weld have a short life.
  • a gas turbine combustion chamber having a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross section.
  • a corrugated component is arranged over the entire cross-sectional circumference of the combustion chamber wall, which forms a plurality of separate resonance chambers with the combustion chamber wall. Openings are introduced in the combustion chamber wall such that in each case a fluid connection between the combustion chamber interior and one of the resonance chambers is provided.
  • the corrugated member has two locking rings which are connected to the combustion chamber wall to seal the resonance spaces.
  • the resonance chambers are thus also designed as cavity resonators. With such a gas turbine combustor, frequencies can be easily damped.
  • Such a corrugated component can also be easily and inexpensively mounted.
  • the corrugated component can be attached over the entire length of the combustion chamber wall. As a result, an efficient damping on the entire length of the combustion chamber wall is possible.
  • the corrugated member may be mounted only on a longitudinal portion of the combustion chamber wall.
  • At least two of the openings present in the combustion chamber wall have a different cross section, wherein each of the at least two openings has a separate fluid connection to at least two separate resonance chambers. This can very easily be used to attenuate different frequencies, such as e.g. when changing from full to partial load occur.
  • the corrugated component bores.
  • cooling air can be introduced into the resonance chamber. This cools both the corrugated member and the combustion chamber wall, e.g. by impingement cooling.
  • the corrugated component has at least two wave troughs.
  • the corrugated component is welded or soldered in these wave troughs with the combustion chamber wall. This ensures in a simple manner that the resonance chambers are separated even with thermal expansion of the corrugated component and / or thermal expansion of the combustion chamber wall. In addition, this represents a simple heat-resistant attachment of the corrugated component to the combustion chamber wall.
  • At least two separate resonance chambers have different volumes. This also different frequencies can be attenuated.
  • FIG. 1 shows in sections a gas turbine combustor 1 according to the invention.
  • the gas turbine combustor 1 has a combustion chamber interior and a combustion chamber wall 2 with a substantially rotationally symmetrical cross section.
  • a corrugated component 3 is arranged over the entire circumference of the combustion chamber wall 2.
  • the corrugated component 3 can be a sheet metal.
  • the component 3 forms with the combustion chamber wall 2 a plurality of separate resonance chambers 5 (FIG. Fig. 2 ) out. Openings 4 ( Fig. 3 ) are introduced in the combustion chamber wall 2 such that in each case a fluid connection between the combustion chamber interior and one of the resonance chambers 5 (FIG. Fig.
  • Each resonance chamber 5 ( Fig. 2 ) is therefore at least one opening 4 ( Fig. 3 ).
  • the corrugated component 3 has two closure rings 6, which are connected to the combustion chamber wall 2, around the resonance chambers 5 (FIG. Fig. 2 ) seal.
  • the two locking rings 6 represent, as it were, a cover of the corrugated component 3, which is otherwise open at both ends. This means that the resonance spaces 5 (FIG. Fig. 2 ) are sealed so to speak by these locking rings 6.
  • the locking rings 6 may be welded or soldered to the combustion chamber wall 2. Likewise, they are additionally soldered or welded to the corrugated component 3.
  • the resonance chambers 5 ( Fig. 2 ) may have different volumes. As a result, different frequencies can be damped.
  • holes 7 may be mounted to realize cooling of the corrugated member 3 but also the combustion chamber wall 2 by means of cooling air through these holes 7.
  • the cooling air passes through the bores 7 into the resonance chambers 5 (FIG. Fig. 2 ) and cools the combustion chamber wall 2, for example by means of impingement cooling.
  • the holes 7 are therefore above the resonance chambers 5 ( Fig. 2 ) appropriate.
  • FIG. 2 shows in sections a cross section of a gas turbine combustor 1 according to the invention with the corrugated component 3.
  • the corrugated component 3 has wave troughs 8. At these wave troughs 8, the corrugated component 3 rests directly on the combustion chamber wall 2.
  • the corrugated component 3 welded to the combustion chamber wall 2 or soldered. This ensures that no fluid connection between the resonance chambers 5 takes place.
  • the welding or soldering can be provided over the entire length of the corrugated component 3.
  • FIG. 3 shows in sections a longitudinal section of a gas turbine combustor 1 according to the invention with corrugated component 3.
  • the existing in the combustion chamber wall 2 openings 4 to at least two separate resonance chambers 5 may have a different cross-section. Thus, different frequencies can be damped.
  • the corrugated member 3 may be mounted on the entire length of the combustion chamber wall 2, or only on a part of the length of the combustion chamber wall 2.

Claims (5)

  1. Chambre de combustion ( 1 ) de turbine à gaz ayant un intérieur de chambre de combustion et une paroi ( 2 ) de chambre de combustion, qui a une section transversale sensiblement de révolution,
    caractérisée en ce que, du côté de la paroi ( 2 ) de la chambre de combustion éloigné de l'intérieur de la chambre de combustion, est disposé un élément ( 3 ) ondulé sur tout le pourtour de section transversale de la paroi ( 2 ) de la chambre de combustion, élément qui forme, avec la paroi ( 2 ) de la chambre de combustion, plusieurs espaces ( 5 ) de résonance distincts et des ouvertures ( 4 ) sont ménagées dans la paroi ( 2 ) de la chambre de combustion de manière à donner respectivement une communication fluidique entre l'intérieur de la chambre de combustion et l'une des chambres ( 5 ) de résonance, l'élément ( 3 ) ondulé ayant deux anneaux ( 6 ) de fermeture, qui sont reliés à la paroi ( 2 ) de la chambre de combustion pour rendre étanche les chambres ( 5 ) de résonance.
  2. Chambre de combustion ( 1 ) de turbine à gaz suivant la revendication 1,
    caractérisée en ce qu'au moins deux ouvertures ( 4 ) présentes dans la paroi ( 2 ) de la chambre de combustion ont une section transversale différente, chacune des au moins deux ouvertures ( 4 ) ayant une communication fluidique distincte avec au moins deux chambres ( 5 ) de résonance distinctes.
  3. Chambre de combustion ( 1 ) de turbine à gaz suivant l'une des revendications précédentes,
    caractérisée en ce que l'élément ( 3 ) ondulé a des creux ( 8 ) d'ondulation entre les chambres ( 5 ) de résonance et l'élément ( 3 ) ondulé est soudé et/ou brasé à la paroi ( 2 ) de la chambre de combustion dans ces creux ( 8 ) d'ondulation.
  4. Chambre de combustion ( 1 ) de turbine à gaz suivant l'une des revendications précédentes,
    caractérisée en ce que l'élément ( 3 ) ondulé a des trous ( 7 ).
  5. Chambre de combustion ( 1 ) de turbine à gaz suivant l'une des revendications précédentes,
    caractérisée en ce qu'au moins deux chambres ( 5 ) de résonance distinctes ont des volumes différents.
EP11158268.0A 2011-03-15 2011-03-15 Chambre de combustion de turbines à gaz Not-in-force EP2500648B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
ES11158268T ES2427440T3 (es) 2011-03-15 2011-03-15 Cámara de combustión de turbina de gas
EP11158268.0A EP2500648B1 (fr) 2011-03-15 2011-03-15 Chambre de combustion de turbines à gaz
US13/414,051 US8464536B2 (en) 2011-03-15 2012-03-07 Gas turbine combustion chamber
RU2012109927/06A RU2012109927A (ru) 2011-03-15 2012-03-14 Камера сгорания газовой турбины
CN201210069388.1A CN102679396B (zh) 2011-03-15 2012-03-15 燃气透平燃烧室

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11158268.0A EP2500648B1 (fr) 2011-03-15 2011-03-15 Chambre de combustion de turbines à gaz

Publications (2)

Publication Number Publication Date
EP2500648A1 EP2500648A1 (fr) 2012-09-19
EP2500648B1 true EP2500648B1 (fr) 2013-09-04

Family

ID=44681478

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11158268.0A Not-in-force EP2500648B1 (fr) 2011-03-15 2011-03-15 Chambre de combustion de turbines à gaz

Country Status (5)

Country Link
US (1) US8464536B2 (fr)
EP (1) EP2500648B1 (fr)
CN (1) CN102679396B (fr)
ES (1) ES2427440T3 (fr)
RU (1) RU2012109927A (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2530685C2 (ru) * 2010-03-25 2014-10-10 Дженерал Электрик Компани Структуры ударного воздействия для систем охлаждения
US8966903B2 (en) * 2011-08-17 2015-03-03 General Electric Company Combustor resonator with non-uniform resonator passages
EP2816288B1 (fr) * 2013-05-24 2019-09-04 Ansaldo Energia IP UK Limited Chambre de combustion de turbine à gaz avec amortisseur de vibrations
CN105157060A (zh) * 2014-05-30 2015-12-16 胡晋青 一种透平燃烧室
CN104676649A (zh) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种阻尼热声振荡声学火焰筒
JP6815735B2 (ja) * 2016-03-03 2021-01-20 三菱パワー株式会社 音響装置、ガスタービン
CN106068054A (zh) * 2016-05-24 2016-11-02 中国人民解放军装备学院 一种流体冷却的气体亚稳态原子束流产生装置
WO2018183078A1 (fr) 2017-03-30 2018-10-04 Siemens Aktiengesellschaft Système avec agencement de conduit pour double utilisation de fluide de refroidissement dans une section de chambre de combustion d'un moteur à turbine à gaz
CN114811649A (zh) * 2022-04-07 2022-07-29 中国联合重型燃气轮机技术有限公司 燃烧室和具有它燃气轮机

Citations (1)

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FR2191025A1 (fr) * 1972-07-04 1974-02-01 Aerospatiale

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US2938333A (en) * 1957-03-18 1960-05-31 Gen Motors Corp Combustion chamber liner construction
GB1010338A (en) * 1962-09-11 1965-11-17 Lucas Industries Ltd Means for supporting the downstream end of a combustion chamber in a gas turbine engine
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners
US3589128A (en) * 1970-02-02 1971-06-29 Avco Corp Cooling arrangement for a reverse flow gas turbine combustor
GB1274414A (en) * 1970-04-20 1972-05-17 Parr Acoustics Ltd Improvements relating to the silencing of boilers
US3702058A (en) * 1971-01-13 1972-11-07 Westinghouse Electric Corp Double wall combustion chamber
US3745766A (en) * 1971-10-26 1973-07-17 Avco Corp Variable geometry for controlling the flow of air to a combustor
US3793827A (en) * 1972-11-02 1974-02-26 Gen Electric Stiffener for combustor liner
US6018950A (en) * 1997-06-13 2000-02-01 Siemens Westinghouse Power Corporation Combustion turbine modular cooling panel
ES2309029T3 (es) 2001-01-09 2008-12-16 Mitsubishi Heavy Industries, Ltd. Camara de combustion de turbina de gas.
JP3962554B2 (ja) * 2001-04-19 2007-08-22 三菱重工業株式会社 ガスタービン燃焼器及びガスタービン
DE50107283D1 (de) * 2001-06-18 2005-10-06 Siemens Ag Gasturbine mit einem Verdichter für Luft
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Also Published As

Publication number Publication date
CN102679396A (zh) 2012-09-19
ES2427440T3 (es) 2013-10-30
CN102679396B (zh) 2015-07-01
US20120234009A1 (en) 2012-09-20
US8464536B2 (en) 2013-06-18
RU2012109927A (ru) 2013-09-20
EP2500648A1 (fr) 2012-09-19

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