EP0597138B1 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0597138B1
EP0597138B1 EP92119124A EP92119124A EP0597138B1 EP 0597138 B1 EP0597138 B1 EP 0597138B1 EP 92119124 A EP92119124 A EP 92119124A EP 92119124 A EP92119124 A EP 92119124A EP 0597138 B1 EP0597138 B1 EP 0597138B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
segments
cooling
burners
gas turbine
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
EP92119124A
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German (de)
English (en)
Other versions
EP0597138A1 (fr
Inventor
Manfred Dr. Aigner
Raphael Urech
Hugo Wetter
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 AG Germany
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP92119124A priority Critical patent/EP0597138B1/fr
Priority to DE59208715T priority patent/DE59208715D1/de
Priority to US08/132,185 priority patent/US5373695A/en
Priority to KR1019930021695A priority patent/KR940011862A/ko
Priority to JP27936693A priority patent/JP3397858B2/ja
Publication of EP0597138A1 publication Critical patent/EP0597138A1/fr
Application granted granted Critical
Publication of EP0597138B1 publication Critical patent/EP0597138B1/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
    • F23R3/02—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 gas turbine combustion chamber according to the preamble of patent claim 1.
  • Combustion chambers of the type mentioned at the outset are known from EP-A1-387 532.
  • the front plate is formed by a single wall on which premixing burners of the double-cone type are arranged.
  • Gas turbine combustion chambers with air-cooled flame tubes are also known, for example from US 4,077,205 or US 3,978,662.
  • the flame tube is essentially constructed from wall parts which overlap in the turbine axial direction. On their side facing away from the combustion chamber, the wall parts each have a plurality of inlet openings distributed over the circumference, via which air is introduced into a distribution chamber arranged in the flame tube and communicating with the combustion chamber.
  • the respective flame tube In the cooling system there, the respective flame tube has a lip which extends over the slot through which the cooling air film emerges. This cooling air film should adhere to the wall of the flame tube in order to form a cooling barrier layer for it.
  • a combustion chamber for a rocket engine in which the combustion chamber inlet is equipped with a plurality of burners which are attached to a front plate, is known from FR-A-2570129.
  • damping chambers which are open on both sides and which communicate with the combustion chamber via passage pipes are arranged in each case in the area of the fuel injection.
  • the invention has for its object to significantly increase the soundproofing of a combustion chamber in a gas turbine combustion chamber of the type mentioned with minimal cooling air consumption by damping the thermo-acoustically fanned vibrations.
  • the advantage of the invention can be seen, inter alia, in the fact that the proximity of the Helmholtz damper to the combustion zones dampens the thermoacoustic vibrations occurring in the flame fronts particularly intensively.
  • the damping tubes in the Helmholtz dampers are designed to be interchangeable, and because the walls of the combustion chamber are provided with a manhole, the dampers can be matched to the vibration to be dampened in the combustion chamber without having to cover the machine.
  • the system essentially consists on the gas turbine side (1) of the rotor 11 bladed with rotor blades and the blade carrier 12 equipped with guide blades.
  • the blade carrier 12 is over projections hooked into corresponding receptacles in the turbine housing 13.
  • the exhaust housing 14 is flanged to the turbine housing 13.
  • the turbine housing 13 also includes the collecting space 15 for the compressed combustion air. From this collecting space, part of the combustion air passes through a perforated cover 30 in the direction of the arrow directly into the annular combustion chamber 3, which in turn enters the turbine inlet, i.e. flows upstream of the first guide row.
  • the compressed air arrives in the collecting space from the diffuser 22 of the compressor 2. Only the last four stages of the latter are shown.
  • the blading of the compressor and the turbine sit on the common shaft 11, the central axis of which represents the longitudinal axis 10 of the gas turbine unit.
  • the combustion chamber 3 is equipped at its head end with premix burners 20, as are known, for example, from EP-A1-387 532.
  • a premix burner shown only schematically in FIG. 2, is a so-called double-cone burner. It essentially consists of two hollow, conical partial bodies 26, 27 which are nested one inside the other in the direction of flow. The respective central axes of the two partial bodies are offset from one another. The adjacent walls of the two partial bodies in their longitudinal extent form tangential slots 28 for the combustion air, which in this way reaches the interior of the burner.
  • a fuel nozzle 29 for liquid fuel is arranged there. The fuel is injected into the hollow cone at an acute angle. The resulting conical liquid fuel profile is enclosed by the combustion air flowing in tangentially.
  • the concentration of the fuel is continuously reduced in the axial direction due to the mixing with the combustion air.
  • the burner can also be operated with gaseous fuel.
  • gaseous fuel for this purpose, in the area of the tangential slots in the walls of the two partial bodies provided in the longitudinal direction of the gas inflow openings.
  • the mixture formation with the combustion air thus begins in the zone of the inlet slots 28.
  • mixed operation with both types of fuel is also possible in this way.
  • a fuel concentration that is as homogeneous as possible is established over the loaded cross-section.
  • a defined dome-shaped return flow zone is created at the burner outlet, at the tip of which the ignition takes place.
  • the combustion gases reach very high temperatures, which places special demands on the combustion chamber walls to be cooled.
  • the annular combustion chamber extends downstream of the burner orifices up to the turbine inlet. It is limited both inside and outside by walls to be cooled, which are usually designed as self-supporting structures.
  • the present combustion chamber is equipped with 72 of the said burners 20. 3, which shows a quarter-circle section, shows the arrangement thereof.
  • Two burners are arranged radially one above the other on a front segment 31. 36 of these adjacent front segments form a closed circular ring, which in this way forms a heat shield.
  • the two burners from adjacent front segments are each radially offset. This means that the radially outer burner of every second front segment directly adjoins the outer ring wall of the combustion chamber, as can also be seen in FIG. 3.
  • the radially inner burners of the other front segments are therefore arranged in the immediate vicinity of the inner ring wall. This results in an uneven thermal load on the corresponding ring walls over the circumference.
  • a rinsed Helmholtz resonator 21 is now housed for soundproofing the combustion chamber.
  • a Helmholtz damper essentially consists of the actual resonance volume 50, an air inlet opening to the Helmholz volume, which is designed here as a feed pipe 51, and a damping pipe 52 opening into the combustion chamber interior. The purge air is drawn from the head space 49 by the damper.
  • the feed tubes 51 are dimensioned such that they cause a relatively high pressure drop for the air flow.
  • the damping tubes 52 allow the air to enter the interior of the combustion chamber with a low residual pressure drop.
  • the limitation of the pressure drop in the damping tubes results from the requirement that even with an uneven pressure distribution on the inside of the combustion chamber wall, an adequate air flow into the combustion chamber always remains guaranteed.
  • hot gas must not enter the Helmholtz resonator in the opposite direction at any point.
  • the choice of the size of the Helmholtz volume 50 results from the requirement that the phase angle between the fluctuations in the damping air mass flows through the supply and damping tubes 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 50 and the openings 51 and 52, is at least the frequency of the combustion chamber vibration to be damped.
  • the volume of the Helmholtz resonator used is preferably at the lowest natural frequency of the combustion chamber is designed. It is also possible to choose an even larger volume. It is thereby achieved that a pressure fluctuation on the inside of the combustion chamber leads to a strongly opposite-phase fluctuation in 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 feed pipe 51 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.
  • 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. 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.
  • 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. Therefore, the highest fluctuation in the reaction rate will also be there, if one takes place.
  • the arrangement of the dampers at the radially outer or inner end of the front segments has a favorable effect, since in this way the respective damper is located in the middle of three burners.
  • the housing of the Helmholtz damper is screwed into the respective front segment 31 from the head space 49 by means of a hollow threaded pin 55.
  • the damping tube 52 protruding into the volume 50 is designed to be exchangeable. For this purpose, it penetrates the hollow threaded pin from the combustion chamber and is latched in the front segment by means of a bayonet lock 53.
  • Spring means 54 ensure that the bayonet catch on the front segment is positively locked.
  • the frequency spectrum is measured with Helmholtz dampers sealed with blind flanges.
  • the required length and inner diameter of the damping tubes can be calculated for a given damping volume.
  • the pipes determined in this way are then installed with the combustion chamber turned off. It goes without saying that several critical vibrations of different frequencies can also be damped in this way by installing different damper tubes.
  • the generally cooled walls of the combustion chamber must be provided with a manhole.
  • these walls are of a special kind in order not to impair the cooling.
  • the thermally highly loaded interior of the combustion chamber is divided into two zones, the walls of which are cooled in different ways.
  • a secondary zone 32 lying downstream and opening into the turbine inlet is delimited by a double-walled flame tube. It consists both on its inner ring 33 and on its outer ring 34 from a flangeless, welded sheet metal construction, which is held together by spacers, not shown. Both rings 33 and 34 are open at their turbine end and form the entrance there for the cooling air.
  • the annular space 35 between the double wall of the outer ring 34 draws the air directly from the collecting space 15, as can be seen in FIG. 1. With efficient convection cooling, the air flows in counterflow to the combustion chamber flow in the direction of the primary zone 36.
  • the annular space 37 between the double wall of the inner ring 33 is supplied with air from a hub diffuser 38.
  • This hub diffuser which connects to the compressor diffuser 22, is delimited on the one hand by a drum cover 24 and on the other hand by an annular shell 39.
  • the latter is connected to the drum cover 24 via ribs (not shown).
  • the air flows in the counterflow to the combustion chamber flow in the direction of the primary zone 36.
  • the cooling of the highly stressed primary zone walls is now carried out by means of individually cooled cooling segments 40. These cooling segments lined up in the circumferential direction and in the axial direction form their flow-limiting wall over the entire axial extent of the primary zone 36. Single cooling has the advantage of a low pressure drop.
  • the thermally highly stressed cooling segments 40 consist of a high-temperature, precision cast alloy. They are suspended in the circumferential direction with two feet 42 each provided with supporting teeth in corresponding grooves in a supporting structure, in a manner similar to how guide vane feet are fastened in blade carriers.
  • this support structure hereinafter referred to as segment carrier 43, consists of two cast half-shells with a horizontal parting plane and not shown claws with which it is supported in the turbine housing.
  • cooling segments 40 arranged side by side in the axial direction corresponds to the number of front segments 31, so that each front segment and a cooling segment is assigned to the burner 20 closest to the wall (FIG. 3).
  • a cooling segment is supplied with cooling air via a radially directed opening 46 which penetrates the segment carrier 43 and connects the collecting space 15 to one end of the cooling chamber 44 lying in the circumferential direction.
  • the outlet opening 47 At the opposite end of this same cooling chamber is the outlet opening 47 in the segment carrier. Both the opening 46 and the outlet opening 47 can either be individual bores or elongated holes that extend in the axial direction over a large part of the segment width.
  • the outlet opening 47 opens into a channel 48 which penetrates the segment carrier 43 in its entire axial extent and is open on both sides.
  • a channel 48 which penetrates the segment carrier 43 in its entire axial extent and is open on both sides.
  • this outer ring is flanged to the segment carrier, the contour of the inner wall being matched to the contour of the cooling segments.
  • the channel 48 opens against a head space 49, which is delimited by the cover 30 and the front segments 31.
  • the cover 30 is also flanged to the segment carrier 43.
  • These axial channels 43 serve to jointly guide the segment cooling air and the cooling air acting on the secondary zone.
  • a about yourself part 143 of the upper half of the segment carrier 43 which extends several cooling segments and forms the above-mentioned manhole, is designed to be removable together with the cooling segments 40 suspended therein.
  • This detachable part 143 of the segment carrier comprises two cooling segments 40 in the circumferential direction and in the axial direction (shown hatched in FIGS. 2 and 3).
  • the part 143 closing the manhole is screwed to the segment carrier 43 by means of a bracket 45 projecting on all sides. It goes without saying that a part of the turbine housing 13 which corresponds to the size of the manhole must also be opened and is therefore designed as an end cover 113.

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  • 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)

Claims (4)

  1. Chambre de combustion pour une turbine à gaz avec un espace de combustion annulaire (32, 36), dont les parois s'étendent depuis l'entrée de la chambre de combustion jusqu'à l'entrée de la turbine à gaz (1), et dans laquelle l'entrée de la chambre de combustion est garnie d'une pluralité de brûleurs (20) uniformément répartis en direction périphérique, qui sont fixés à une plaque frontale, caractérisée en ce que des atténuateurs de Helmholtz à balayage (21), composés d'un tube d'alimentation (51), d'un volume de résonance (50) et d'un tube d'amortissement (52), sont disposés dans la région des brûleurs (20), les tubes d'amortissement (52) débouchant à l'intérieur de la chambre de combustion et étant interchangeables depuis cet endroit, les parois de l'espace de combustion étant pourvues d'un trou d'homme à cet effet.
  2. Chambre de combustion pour turbine à gaz suivant la revendication 1, caractérisée en ce que la plaque frontale se compose de plusieurs segments avant (31) alignés l'un avec l'autre en direction périphérique en un anneau circulaire, en ce que les brûleurs (20) sont fixés par deux respectivement à un segment avant (31) en étant radialement superposés, et en ce que les brûleurs de segments avant voisins sont décalés radialement l'un par rapport à l'autre, les atténuateurs de Helmholtz (21) étant disposés radialement au-dessus des brûleurs sur une première moitié des segments avant et radialement en dessous des brûleurs sur l'autre moitié des segments avant.
  3. Chambre de combustion pour une turbine à gaz suivant la revendication 1, caractérisée
    - en ce que dans une zone primaire (36) de l'espace de combustion, une pluralité de segments de refroidissement (40) refroidis individuellement forment la paroi de limitation de l'écoulement, et dans laquelle les segments de refroidissement sont suspendus dans un porte-segments (43) composé de deux demi-coquilles avec un plan de séparation horizontal, porte-segment qui forme la séparation extérieure de la zone primaire vers une chambre de collecte (15) guidant l'air de combustion comprimé,
    - en ce qu'une zone secondaire (32) située en aval est délimitée par un tube de flammes (33, 34) à double paroi dont l'extrémité d'entrée du côté de la turbine est ouverte et forme l'entrée pour l'air de refroidissement de la zone secondaire;
    - en ce que l'air de refroidissement provenant de la zone primaire (36) et de la zone secondaire (32) est fourni en commun à l'entrée du brûleur, des canaux axiaux (48) communiquant avec l'entrée du brûleur étant disposés à cet effet dans le porte-segment (43); et
    - en ce qu'une pièce (143) de la moitié supérieure du porte-segment (43), s'étendant au-dessus de plusieurs segments de refroidissement et formant le trou d'homme, est réalisée de façon amovible en même temps que les segments de refroidissement (40) qui y sont suspendus.
  4. Chambre de combustion pour turbine à gaz suivant la revendication 3, caractérisée
    - en ce que le nombre des segments de refroidissement (40) alignés l'un avec l'autre en direction périphérique correspond au nombre de segments avant (31) et en ce qu'au moins trois segments de refroidissement sont disposés l'un à côté de l'autre en direction axiale;
    - et en ce que la pièce amovible (143) du porte-segment (43) embrasse deux segments de refroidissement en direction périphérique et en direction axiale.
EP92119124A 1992-11-09 1992-11-09 Chambre de combustion pour turbine à gaz Expired - Lifetime EP0597138B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP92119124A EP0597138B1 (fr) 1992-11-09 1992-11-09 Chambre de combustion pour turbine à gaz
DE59208715T DE59208715D1 (de) 1992-11-09 1992-11-09 Gasturbinen-Brennkammer
US08/132,185 US5373695A (en) 1992-11-09 1993-10-06 Gas turbine combustion chamber with scavenged Helmholtz resonators
KR1019930021695A KR940011862A (ko) 1992-11-09 1993-10-19 가스 터빈 연소실
JP27936693A JP3397858B2 (ja) 1992-11-09 1993-11-09 ガスタービンの燃焼室

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92119124A EP0597138B1 (fr) 1992-11-09 1992-11-09 Chambre de combustion pour turbine à gaz

Publications (2)

Publication Number Publication Date
EP0597138A1 EP0597138A1 (fr) 1994-05-18
EP0597138B1 true EP0597138B1 (fr) 1997-07-16

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP92119124A Expired - Lifetime EP0597138B1 (fr) 1992-11-09 1992-11-09 Chambre de combustion pour turbine à gaz

Country Status (5)

Country Link
US (1) US5373695A (fr)
EP (1) EP0597138B1 (fr)
JP (1) JP3397858B2 (fr)
KR (1) KR940011862A (fr)
DE (1) DE59208715D1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6370863B2 (en) 1998-07-27 2002-04-16 Asea Brown Boveri Ag Method of operating a gas-turbine chamber with gaseous fuel
EP1235033A2 (fr) 2001-02-22 2002-08-28 ALSTOM (Switzerland) Ltd Chambre de combustion annulaire et méthode d'opération de la dite chambre
US6694745B2 (en) 2001-06-22 2004-02-24 Alstom Technology Ltd Method for running up a gas turbine plant
EP1655468A2 (fr) 2004-11-03 2006-05-10 ALSTOM Technology Ltd Soupape de carburant pour l'opération d'un système de bruleur de turbine à gaz et système de bruleur comprenant une telle soupape
DE102006053278A1 (de) * 2006-11-03 2008-05-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammervorrichtung
EP2474784A1 (fr) 2011-01-07 2012-07-11 Siemens Aktiengesellschaft Système de combustion pour turbine à gaz comprenant un résonateur
DE102005062284B4 (de) 2005-12-24 2019-02-28 Ansaldo Energia Ip Uk Limited Brennkammer für eine Gasturbine

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DE4411624A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Brennkammer mit Vormischbrennern
US5644918A (en) * 1994-11-14 1997-07-08 General Electric Company Dynamics free low emissions gas turbine combustor
US5685157A (en) * 1995-05-26 1997-11-11 General Electric Company Acoustic damper for a gas turbine engine combustor
DE19523094A1 (de) * 1995-06-26 1997-01-02 Abb Management Ag Brennkammer
DE19640980B4 (de) * 1996-10-04 2008-06-19 Alstom Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
ATE232287T1 (de) * 1997-07-15 2003-02-15 Alstom Switzerland Ltd Schwingungsdämpfende brennkammerwandstruktur
DE59709155D1 (de) * 1997-07-15 2003-02-20 Alstom Switzerland Ltd Vorrichtung zur Dämpfung von Brennkammerschwingungen
US6464489B1 (en) * 1997-11-24 2002-10-15 Alstom Method and apparatus for controlling thermoacoustic vibrations in a combustion system
SE9802707L (sv) * 1998-08-11 2000-02-12 Abb Ab Brännkammaranordning och förfarande för att reducera inverkan av akustiska trycksvängningar i en brännkammaranordning
DE59809097D1 (de) 1998-09-30 2003-08-28 Alstom Switzerland Ltd Brennkammer für eine Gasturbine
DE19851636A1 (de) * 1998-11-10 2000-05-11 Asea Brown Boveri Dämpfungsvorrichtung zur Reduzierung der Schwingungsamplitude akustischer Wellen für einen Brenner
US6351947B1 (en) 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
DE10026121A1 (de) * 2000-05-26 2001-11-29 Alstom Power Nv Vorrichtung zur Dämpfung akustischer Schwingungen in einer Brennkammer
US6530221B1 (en) 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
DE10058688B4 (de) * 2000-11-25 2011-08-11 Alstom Technology Ltd. Dämpferanordnung zur Reduktion von Brennkammerpulsationen
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
CA2399534C (fr) * 2001-08-31 2007-01-02 Mitsubishi Heavy Industries, Ltd. Turbine a gaz et chambre de combustion connexe
KR100804951B1 (ko) * 2001-11-27 2008-02-20 주식회사 포스코 가스터빈 연소기의 충격흡수장치
EP1466124B1 (fr) 2002-01-14 2008-09-03 ALSTOM Technology Ltd ENSEMBLE DE BRûLEURS POUR CHAMBRE DE COMBUSTION ANNULAIRE DE TURBINE à GAZ
EP1476699B1 (fr) 2002-01-16 2013-11-13 Alstom Technology Ltd Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz
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
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
GB2396687A (en) * 2002-12-23 2004-06-30 Rolls Royce Plc Helmholtz resonator for combustion chamber use
GB0305025D0 (en) * 2003-03-05 2003-04-09 Alstom Switzerland Ltd Method and device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
US7272931B2 (en) * 2003-09-16 2007-09-25 General Electric Company Method and apparatus to decrease combustor acoustics
ITTO20031013A1 (it) 2003-12-16 2005-06-17 Ansaldo Energia Spa Sistema di smorzamento di instabilita' termoacustiche in un dispositivo combustore per una turbina a gas.
ES2616873T3 (es) 2004-03-31 2017-06-14 Ansaldo Energia Ip Uk Limited Disposición de múltiples quemadores para hacer funcionar una cámara de combustión así como procedimiento para hacer funcionar la disposición de múltiples quemadores
US7464552B2 (en) * 2004-07-02 2008-12-16 Siemens Energy, Inc. Acoustically stiffened gas-turbine fuel nozzle
US7334408B2 (en) * 2004-09-21 2008-02-26 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
EP1703208B1 (fr) * 2005-02-04 2007-07-11 Enel Produzione S.p.A. Amortissement des oscillations thermoacoustiques dans des chambres de combustion de turbine à gaz avec chambre annulaire
US7413053B2 (en) * 2006-01-25 2008-08-19 Siemens Power Generation, Inc. Acoustic resonator with impingement cooling tubes
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US5373695A (en) 1994-12-20
JPH06221563A (ja) 1994-08-09
JP3397858B2 (ja) 2003-04-21
DE59208715D1 (de) 1997-08-21
EP0597138A1 (fr) 1994-05-18
KR940011862A (ko) 1994-06-22

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