EP1137899B1 - Dispositif de combustion et procede de combustion d'un combustible - Google Patents

Dispositif de combustion et procede de combustion d'un combustible Download PDF

Info

Publication number
EP1137899B1
EP1137899B1 EP99964516A EP99964516A EP1137899B1 EP 1137899 B1 EP1137899 B1 EP 1137899B1 EP 99964516 A EP99964516 A EP 99964516A EP 99964516 A EP99964516 A EP 99964516A EP 1137899 B1 EP1137899 B1 EP 1137899B1
Authority
EP
European Patent Office
Prior art keywords
combustion
fuel
flow
combustion device
region
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.)
Revoked
Application number
EP99964516A
Other languages
German (de)
English (en)
Other versions
EP1137899A1 (fr
Inventor
Günther SCHULZE
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=8233108&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1137899(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP99964516A priority Critical patent/EP1137899B1/fr
Publication of EP1137899A1 publication Critical patent/EP1137899A1/fr
Application granted granted Critical
Publication of EP1137899B1 publication Critical patent/EP1137899B1/fr
Anticipated expiration legal-status Critical
Revoked legal-status Critical Current

Links

Images

Classifications

    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/161—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general in systems with fluid flow
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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 combustion device for combustion a fuel, the fuel being a Fluid flow can be fed to the combustion via a feed channel is.
  • the invention also relates to a corresponding method.
  • outflow processes are described in chapter 5.6.
  • Outflow processes of a fluid from a container in which the fluid is stored at pressure p i and density ⁇ i are shown in more detail.
  • the fluid exits the container as a jet, the jet pressure p a prevailing in the jet.
  • the pressure ratio at which the given container state - i.e. given container pressure ⁇ i and given fluid density ⁇ i and given container opening from which the fluid exits - the mass flow of the fluid no longer changes as the critical pressure ratio (p a / p i ) (k) .
  • p a / p i Depending on the size of the pressure ratio p a / p i, a distinction is made between two types of outflow processes: 1. Subcritical outflow; 2. Supercritical outflow.
  • a Laval nozzle is described in section 5.6.2 of the same book.
  • the Laval nozzle serves the outflowing fluid to expand beyond the critical pressure ratio and thus the flow velocity over the speed of sound increase beyond.
  • the fluid is first of all compresses a narrowing channel, the Flow rate increased to the speed of sound.
  • An expanding channel section follows in which the fluid expands and the flow rate Supersonic range reached.
  • Such a Laval nozzle serves e.g. to achieve maximum outflow speeds for shear gases of rocket engines.
  • the Laval nozzle is behaving here like a venturi tube. For the definition of a Venturi tube follow further details below.
  • Section 5.7 of the same book contains compression flows described.
  • Section 5.7.1 explains how a Subsonic diffuser.
  • Subsonic diffusers are in the direction of flow extended channels, one in the subsonic area current is delayed. Through the Delay there is an increase in pressure.
  • Subsonic diffusers can be found, for example, in jet devices, venturi tubes and in the idlers and outlet housings of turbocompressors.
  • Section 5.7.2 describes a supersonic diffuser where the channel cross-section changes in the direction of flow narrows.
  • the European standard EN ESO 5167-1 concerns flow measurements of fluids with throttling devices.
  • part 1 are bezels, Nozzles and Venturi tubes in fully flowed lines with Circular cross section described.
  • Figure 10 shows a classic one Venturi tube.
  • the Venturi tube flows along a flow direction a fluid.
  • the venturi tube consists of one narrowing in the flow direction inlet cone and a adjoining the inlet cone in the direction of flow, widening outlet cone.
  • A is created in the inlet cone large pressure loss. This is through the outlet cone Pressure loss made up for the most part, so that the overall through the Venturi tube compared to a tube with unchangeable Cross section and the same length Pressure loss remains small.
  • EP-A-122 526 discloses a fuel lance that operates simultaneously both the decoupling of the fuel line to avoid of combustion vibrations as well as the possibility fuel regulation.
  • the fuel lance carries an adjustable, with fuel passage openings provided throttle body, the penetration depth compared to that solid body a measure of the amount of fuel flowing through is.
  • the object of the invention is to provide a combustion device, those in terms of control and influence the spread and formation of a burn induced sound waves has favorable properties.
  • Another object of the invention is to provide a corresponding Process.
  • this object is achieved by specifying a Combustion device for burning fuel with a supply channel for supplying the fuel to one Combustion zone, with the fuel as a fluid stream a flow direction and one in a nominal operating interval nominal speed through the feed channel is feasible and wherein the supply channel in a decoupling area is narrowed, the decoupling area as one continuous narrowing of the feed channel along the flow direction is designed so that from the combustion zone Sound waves running in the fluid flow against the direction of flow at least at the nominal speed in the decoupling area partially reflected.
  • combustion vibrations can result arise that with a fluctuation in a power release a pressure pulse occurs in the fluid flow during combustion.
  • a pressure pulse in the fluid stream in turn has one Non-uniformity in the mass flow into the combustion zone resulting fluid flow. This leads to again a fluctuating release of power during combustion.
  • the geometric designs of the feed channel it can help build positive feedback between pressure pulses in the fluid flow and the fluctuating Power release when combustion comes. It forms a combustion oscillation.
  • Such a combustion vibration can e.g. as a significant noise pollution disruptive.
  • the Invention is based on the knowledge that the spread of sound waves in the fuel via the feed channel into further, acoustically coupled areas the tendency to training such combustion vibrations favored.
  • a acoustic decoupling of the feed channel or several This mechanism prevents fuel supply channels.
  • Such an acoustic decoupling is by a Narrowing of the feed channel or feed channels reached.
  • narrowing in the direction of flow increases Flow velocity of the fluid.
  • the flow rate can be increased so far that contrary to the Direction of flow against the narrowing sound waves be reflected.
  • the constriction is designed so that at a nominal velocity of the fluid flow in the supply channel at the constriction such a high acceleration of the Fluids reveals that a high proportion of those against the narrowing current sound waves is reflected.
  • the nominal speed lies e.g. within a speed interval, such operating conditions of the combustion device corresponds to those with a high tendency to training of combustion vibrations.
  • the decoupling area is considered a continuous one Narrowing of the feed channel along the flow direction educated. Result from such a continuous narrowing less than a discontinuous narrowing Flow and pressure losses due to turbulence.
  • a such continuous narrowing could e.g. B. something like that be trained, such as that in the above-mentioned book by Willi Bohl described supersonic diffuser.
  • a pressure increase area the one Expansion of the feed channel corresponds.
  • the Passage from the decoupling area and pressure increase area corresponds to e.g. that in the European given above Standard Venturi tube or a Laval nozzle.
  • Such a configuration is particularly advantageous if when a high fluid mass flow has to be provided.
  • the fuel is preferably natural gas or oil.
  • the combustion zone is preferably located in a combustion chamber.
  • the combustion chamber can have any shape, special meaning but comes a tubular or an annular Combustion chamber too.
  • Combustion vibrations can occur in a combustion chamber through an interaction of a fluctuation in performance in the combustion and acoustic modes of the Form the combustion chamber.
  • Such combustion chamber vibrations can spread out in fluidically coupled rooms, e.g. into the supply lines of fuel or air and possibly up to a supply pump, which makes it mechanically strong can be loaded.
  • An acoustic decoupling by means of the tapering of the feed channel prevents such Propagation of combustion chamber vibrations.
  • the Tendency to develop combustion chamber vibrations at all reduced, because the available for the combustion chamber vibrations standing acoustic resonance space by decoupling the feed channel is reduced.
  • the combustion device is preferably a gas turbine, especially with an annular combustion chamber.
  • a gas turbine With a gas turbine there is a particularly high level of power release the combustion.
  • Combustion vibrations can be here to particularly large noise pollution and damaging vibrations to lead.
  • There are acoustic modes in an annular combustion chamber due to the complicated geometry practically unpredictable, so that the formation of combustion chamber vibrations is particularly difficult to prevent here.
  • the acoustic decoupling between the ring combustion chamber and the feed channels the combustion media is of particular importance here.
  • the object is also achieved according to the invention by giving a method of burning fuel, the Fuel as a fluid flow with a flow direction a flow direction and one in a nominal operating interval nominal speed fed to a combustion zone is and wherein the fluid flow in a decoupling area is tapered, the fluid flow in the flow direction is continuously narrowed so that from the combustion zone running in the fluid flow against the direction of flow Sound waves at the nominal speed in the decoupling area be at least partially reflected.
  • the fluid flow is preferably continuous in the flow direction narrows.
  • the pressure in the Fluid flow through one following the constriction Expansion of the fluid flow increases. It is further preferred as Natural gas or oil used as fuel.
  • FIG. 1 shows a combustion device 1.
  • a Cross-section circular air duct 3 is also in the Cross section of circular fuel channel 5, which is a supply channel 5, arranged concentrically.
  • air 6 in the form of an air stream 7 with a Flow direction 8 out.
  • fuel channel 5 is as Fluid flow 9 along a flow direction 10 fuel 14, e.g. Oil, led out of a fuel tank 12.
  • the Air 6 and the fuel 14 are in a combustion zone 11 burned in a flame 13.
  • a fluctuation in the power release during the combustion a sound wave calls 15 in the fluid flow 9 of the fuel 14. This sound wave 15 migrates against the direction of flow 10 in Fluid stream 9 upstream.
  • the sound wave 15 could enforce the entire feed channel 5 and approximately to one Fuel pump, not shown, and wander if necessary damage.
  • the combustion zone 11 by means of the feed channel 5 considerably extended rooms acoustically coupled, due to the combustion vibrations in the combustion device 1 could spread and also the resonance rooms represent the formation of combustion vibrations can favor.
  • the decoupling area 17 is due to a narrowing of the feed channel 5 is formed along the flow direction 10.
  • the flow velocity is thus in the decoupling area 17 of the fluid flow 9 increased.
  • the decoupling area 17 is designed so that at a nominal speed of Fluid flow 9 in the feed channel 5 this flow rate is greatly increased in the decoupling area 17, preferably to a value close to the speed of sound in the fluid flow.
  • the remaining one Part continues as the residual sound wave 21 the feed channel 5 upstream.
  • the nominal speed is in one Nominal operating interval, which is an interval of operating states close to a full load and a full load state.
  • the full load state of the combustion device 1 is the maximum value for a power release during combustion. In operating conditions of the combustion device 1, the less power release than a full load correspond, there is less reflection of the Sound wave 15. Combustion vibrations can be special be disturbing and harmful near full load, because there is a high level of power release here. With less Load conditions is therefore less reflection of the Sound wave 15 and thus a higher spread of the sound wave 15 acceptable.
  • Connects to the decoupling area 17 a pressure increase area 23.
  • the decoupling area 17 forms a reflection section together with the pressure increasing area 23 24 with a length 24 of the feed channel 5.
  • the pressure increase area 23 corresponds to an expansion of the Feed channel 5, in this case on the cross section of the feed channel 5, which is also in the flow direction 10 before the decoupling area 17 is present.
  • the reflection section 24 is a venturi tube.
  • the pressure increasing area 23 is preferred designed so that at the nominal speed maximum pressure increase in the fluid flow 9 results.
  • the decoupling area 17 has an entry area 25 and one End area 27 on. The end region 27 is on at the same time Entry area 29 of the pressure increase area 23.
  • the pressure increase area 23 ends at an exit area 31 schematic representation of the pressure curve in the decoupling area 17 and in the pressure increase area 23 is also in the figure 1 added.
  • FIG. 2 shows schematically a gas turbine Combustion device 1.
  • a Compressor 45 and a turbine 47 are arranged.
  • a combustion chamber 49 is connected, which is designed as an annular combustion chamber.
  • the burner 51 has an air duct 3, which is fluidically connected the compressor 45 is connected.
  • the burner 51 continues to point a supply channel 5 for supplying natural gas 14.
  • combustion media So here are air 6 from the compressor 45 and Natural gas 14. These burn in the combustion chamber 49.
  • Hot fuel gases 53 generated drive the turbine 47 on. Due to the great power release in such Gas turbine 1 can with special combustion vibrations large amplitudes arise.
  • Such combustion vibrations can occur as combustion chamber vibrations in the combustion chamber 49 form.
  • a decoupling area 17 is provided in the feed channel 5. On this a pressure increase area closes in the direction of flow 23 on.
  • the effects and advantages of the decoupling area 17 and the pressure increasing area 23 correspond to the to Figure 1 explained.
  • the natural gas supply system, not shown is therefore effective acoustically from the combustion chamber 49 decoupled.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid Mechanics (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Feeding And Controlling Fuel (AREA)

Abstract

L'invention concerne un dispositif de combustion (1) destiné à la combustion du combustible (14), et comprenant un canal d'amenée (5) destiné à l'alimentation en combustible (14) d'une zone de combustion (11). Le combustible (14) peut être acheminé dans le canal d'amenée (5) sous la forme d'un flux fluidique (9) dans une direction d'écoulement (10) et à une vitesse nominale située dans une plage de fonctionnement nominal. Dans la zone de découplage (17), le canal d'amenée (5) est rétréci de telle façon que les ondes sonores (15) se propageant de la zone de combustion (11) dans le flux fluidique (9) à l'encontre de la direction d'écoulement (10) sont au moins partiellement réfléchies dans cette zone de découplage (17) à la vitesse nominale.

Claims (14)

  1. Dispositif (1) de combustion de combustible (14) comprenant un canal (5) d'entrée pour apporter du combustible (14) à une zone (11) de combustion, le combustible (14) pouvant passer dans le canal (5) d'entrée dans un courant (9) de fluide ayant un sens (10) du courant et une vitesse nominale se trouvant dans un intervalle de fonctionnement nominal, le canal (5) d'entrée étant rétréci dans une partie (17) de découplage, caractérisé en ce que la partie (17) de découplage est constituée sous la forme d'un rétrécissement continu du canal (5) le long du sens (10) du courant de façon à ce que des ondes (15) acoustiques allant de la zone (11) de combustion dans le courant (9) de fluide à l'encontre du sens (10) du courant soient réfléchies au moins en partie dans la partie (17) de découplage à la vitesse nominale.
  2. Dispositif (1) de combustion suivant la revendication 1, caractérisé en ce que le canal (5) d'entrée a une section transversale circulaire ou annulaire.
  3. Dispositif (1) de combustion suivant la revendication 1 ou 2, caractérisé en ce qu'il fait suite, dans le sens (10) du courant à la partie (17) de découplage, une partie (23) d'augmentation de la pression dans laquelle le canal (5) d'entrée s'élargit.
  4. Dispositif (1) de combustion suivant la revendication 3, caractérisé en ce que la partie (17) de découplage forme avec la partie (23) d'augmentation de la pression un tronçon (22) de réflexion qui est constitué sous la forme d'une buse de Laval.
  5. Dispositif (1) de combustion suivant la revendication 3, caractérisé en ce que la partie (17) de découplage forme, ensemble, avec la partie (23) d'augmentation de la pression un tronçon (22) de réflexion qui est constitué sous la forme d'un tube Venturi.
  6. Dispositif (1) de combustion suivant l'une des revendications précédentes, caractérisé en ce que le combustible est du gaz naturel ou du pétrole.
  7. Dispositif (1) de combustion suivant l'une des revendications précédentes, caractérisé en que la zone (11) de combustion se trouve dans une chambre (49) de combustion.
  8. Dispositif (1) de combustion suivant la revendication 7, caractérisé par une réalisation sous la forme d'une turbine à gaz.
  9. Dispositif (1) de combustion suivant la revendication 7 ou 8, caractérisé en ce que la chambre (49) de combustion est réalisée sous la forme d'une chambre de combustion annulaire.
  10. Dispositif (1) de combustion suivant l'une des revendications précédentes,
    dans laquelle l'intervalle de fonctionnement nominal est un intervalle de pleine charge qui comprend les états de fonctionnement pour lesquels une énergie pouvant être transformée lors de la combustion est au moins à peu près maximum, caractérisé en ce que la partie (17) de découplage est rétrécie de façon à ce que, dans l'intervalle de pleine charge, une plus grande proportion d'ondes (15) acoustiques est réfléchie que dans d'autres états.
  11. Procédé de combustion d'un combustible (14), dans lequel on envoie à une zone (11) de combustion un courant (9) de fluide ayant un sens (10) du courant et une vitesse nominate se trouvant dans un intervalle de fonctionnement nominal, le courant (9) de fluide étant rétréci dans une partie (17) de découplage, caractérisé en ce que l'on rétrécit continuellement le courant (9) de fluide dans le sens (8, 10) du courant de façon à ce que des ondes (15) acoustiques allant de la zone (11) de combustion dans le courant (9) de fluide à l'encontre du sens (8, 10) du courant soient réfléchies pour la vitesse nominale dans la partie (17) de découplage.
  12. Procédé suivant la revendication 11, caractérisé en ce que l'on élargit le courant (9) de fluide à la suite du rétrécissement et on augmente ainsi la pression dans le courant (9) de fluide.
  13. Procédé suivant la revendication 11 ou 12, caractérisé en ce qu'on utilise comme combustible (14) du gaz naturel ou du pétrole.
  14. Procédé suivant la revendication 11, 12 ou 13, caractérisé en ce que l'on brûle le combustible (14) dans une chambre (49) de combustion, notamment dans une chambre de combustion annulaire d'une turbine (1) à gaz.
EP99964516A 1998-12-08 1999-12-01 Dispositif de combustion et procede de combustion d'un combustible Revoked EP1137899B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP99964516A EP1137899B1 (fr) 1998-12-08 1999-12-01 Dispositif de combustion et procede de combustion d'un combustible

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP98123359 1998-12-08
EP98123359 1998-12-08
PCT/EP1999/009401 WO2000034714A1 (fr) 1998-12-08 1999-12-01 Dispositif de combustion et procede de combustion d'un combustible
EP99964516A EP1137899B1 (fr) 1998-12-08 1999-12-01 Dispositif de combustion et procede de combustion d'un combustible

Publications (2)

Publication Number Publication Date
EP1137899A1 EP1137899A1 (fr) 2001-10-04
EP1137899B1 true EP1137899B1 (fr) 2003-11-12

Family

ID=8233108

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99964516A Revoked EP1137899B1 (fr) 1998-12-08 1999-12-01 Dispositif de combustion et procede de combustion d'un combustible

Country Status (5)

Country Link
US (1) US6615587B1 (fr)
EP (1) EP1137899B1 (fr)
JP (1) JP2002531805A (fr)
DE (1) DE59907751D1 (fr)
WO (1) WO2000034714A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
US6820431B2 (en) * 2002-10-31 2004-11-23 General Electric Company Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly
EP2110602A1 (fr) * 2008-04-16 2009-10-21 Siemens Aktiengesellschaft Découplage partiel acoustique destiné à réduire des oscillations de flammes à auto-induction
US20100089065A1 (en) * 2008-10-15 2010-04-15 Tuthill Richard S Fuel delivery system for a turbine engine
JP5448762B2 (ja) * 2009-12-02 2014-03-19 三菱重工業株式会社 ガスタービン用燃焼バーナ
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
DE212013000118U1 (de) * 2012-05-15 2015-01-30 Andritz Technology And Asset Management Gmbh Zellstofftrockner mit Blaskästen zum Trocknen einer Zellstoffbahn
JP5762481B2 (ja) * 2013-07-16 2015-08-12 三菱日立パワーシステムズ株式会社 燃料ノズル、これを備えた燃焼器及びガスタービン

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3958413A (en) * 1974-09-03 1976-05-25 General Motors Corporation Combustion method and apparatus
EP0122526B1 (fr) * 1983-04-13 1987-05-20 BBC Aktiengesellschaft Brown, Boveri & Cie. Injecteur de combustible pour la chambre de combustion d'une turbine à gaz
US4835962A (en) * 1986-07-11 1989-06-06 Avco Corporation Fuel atomization apparatus for gas turbine engine
GB2224315B (en) 1988-08-10 1992-09-02 Fawcett Christie Hydraulics Li Hydraulic noise attenuators
JPH07501137A (ja) 1991-11-15 1995-02-02 シーメンス アクチエンゲゼルシヤフト ガスタービン設備の燃焼室内の燃焼振動抑制装置
US5211004A (en) * 1992-05-27 1993-05-18 General Electric Company Apparatus for reducing fuel/air concentration oscillations in gas turbine combustors
US5319931A (en) * 1992-12-30 1994-06-14 General Electric Company Fuel trim method for a multiple chamber gas turbine combustion system
DE4430697C1 (de) * 1994-08-30 1995-09-14 Freudenberg Carl Fa Zuluftschalldämpfer
NL1000492C1 (nl) 1995-06-02 1996-12-03 Q E International Bv Geluidsdemper, een hiermee uitgeruste cokesovengasinstallatie, en een schot voor de geluidsdemper.

Also Published As

Publication number Publication date
WO2000034714A1 (fr) 2000-06-15
EP1137899A1 (fr) 2001-10-04
US6615587B1 (en) 2003-09-09
JP2002531805A (ja) 2002-09-24
DE59907751D1 (de) 2003-12-18

Similar Documents

Publication Publication Date Title
EP1481195B1 (fr) Bruleur, procede de fonctionnement d'un bruleur et turbine a gaz
DE19903770B4 (de) Vergasungsbrenner für einen Gasturbinenmotor
DE60105531T2 (de) Gasturbinenbrennkammer, Gasturbine und Düsentriebwerk
EP1224423B1 (fr) Bruleur
DE4418014A1 (de) Verfahren zum Fördern und Vermischen eines ersten Fluids mit einem zweiten, unter Druck stehenden Fluid
EP0576717A1 (fr) Chambre de combustion de turbine à gaz
DE102009026056A1 (de) Brennkammerstruktur
CH697709B1 (de) Brennkammer mit gekühltem Venturirohr.
EP1342953A1 (fr) Turbine à gaz
EP1137899B1 (fr) Dispositif de combustion et procede de combustion d'un combustible
DE102016106984A1 (de) Systeme und Verfahren zur Steuerung der Verbrennungsdynamik in einem Verbrennungssystem
DE102008002934A1 (de) Brennstoffdüse für ein Gasturbinentriebwerk und Verfahren zur Herstellung desselben
EP2260238B1 (fr) Procédé de fonctionnement d'un brûleur à prémélange
DE3023900A1 (de) Diffusorvorrichtung und damit ausgeruestetes gasturbinentriebwerk
CH697802A2 (de) Leckagen reduzierendes Venturi-Rohr für trockene Stickoxid-(NOx)-Niedrigemissions-Brenner.
EP1892472B1 (fr) Système de combustion en particulier pour une turbine à gaz
EP2187125A1 (fr) Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
DE112017001100T5 (de) Akustische vorrichtung und gasturbine
EP0845639B1 (fr) Chambre de combustion et méthode d'exploitation
EP1114967B1 (fr) Procédé et dispositif pour supprimer les tourbillons dans une chambre à combustion d'une turbomachine
DE10352252B4 (de) Kompressor für eine Turbogruppe
EP3473930A1 (fr) Buse pour une chambre de combustion d'un propulseur
EP1240421B1 (fr) Turboreacteur
WO2009127507A1 (fr) Découplage acoustique partiel destiné à réduire les oscillations de flamme auto-induites
DE102018211907A1 (de) Luftversorgungssystem für ein Luftfahrzeug

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

17P Request for examination filed

Effective date: 20010516

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

17Q First examination report despatched

Effective date: 20021213

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

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): CH DE FR GB IT LI

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SERVOPATENT GMBH

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 59907751

Country of ref document: DE

Date of ref document: 20031218

Kind code of ref document: P

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: GERMAN

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20040117

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

ET Fr: translation filed
PLBQ Unpublished change to opponent data

Free format text: ORIGINAL CODE: EPIDOS OPPO

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: ALSTOM TECHNOLOGY LTD.

Effective date: 20040812

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

PLCK Communication despatched that opposition was rejected

Free format text: ORIGINAL CODE: EPIDOSNREJ1

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

APBQ Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3O

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

Ref country code: IT

Payment date: 20071219

Year of fee payment: 9

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

Ref country code: GB

Payment date: 20071213

Year of fee payment: 9

Ref country code: FR

Payment date: 20071219

Year of fee payment: 9

Ref country code: CH

Payment date: 20080304

Year of fee payment: 9

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

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

Ref country code: DE

Payment date: 20080218

Year of fee payment: 9

RDAF Communication despatched that patent is revoked

Free format text: ORIGINAL CODE: EPIDOSNREV1

RDAG Patent revoked

Free format text: ORIGINAL CODE: 0009271

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

Free format text: STATUS: PATENT REVOKED

27W Patent revoked

Effective date: 20080417

GBPR Gb: patent revoked under art. 102 of the ep convention designating the uk as contracting state

Effective date: 20080417

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL