EP1524469A1 - Brûleur à prémélange pour une turbine à gaz - Google Patents

Brûleur à prémélange pour une turbine à gaz Download PDF

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Publication number
EP1524469A1
EP1524469A1 EP03023211A EP03023211A EP1524469A1 EP 1524469 A1 EP1524469 A1 EP 1524469A1 EP 03023211 A EP03023211 A EP 03023211A EP 03023211 A EP03023211 A EP 03023211A EP 1524469 A1 EP1524469 A1 EP 1524469A1
Authority
EP
European Patent Office
Prior art keywords
burner
premix
gas turbine
gas
adjusting device
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.)
Withdrawn
Application number
EP03023211A
Other languages
German (de)
English (en)
Inventor
Hans Maghon
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 EP03023211A priority Critical patent/EP1524469A1/fr
Publication of EP1524469A1 publication Critical patent/EP1524469A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/02—Structural details of mounting
    • F23C5/06—Provision for adjustment of burner position during operation
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/22—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants movable, e.g. to an inoperative position; adjustable, e.g. self-adjusting
    • 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 premix burner of a gas turbine,
  • a gas turbine in heavy construction with a Combustion chamber, in particular an annular combustion chamber or a cylindrical combustion chamber, at least one burner is provided, and at the at a fuel gas outlet of the Brenners a Vormischgasbrennkanal is attached.
  • the invention further relates to the use of such a premix burner in a gas turbine, in particular a gas turbine in heavy construction, as well as a method for flame stabilization on a premix burner of a gas turbine.
  • Premix burners of modern gas turbines tend to be high Flame temperatures to a combustion instability, the For example, due to self-excited combustion oscillations can surrender and in a "drone" on Premix burner expresses.
  • the instability of combustion arises as has now been stated, by a Feedback between the power release in the flame and the acoustics in the (ring) combustion chamber of the burner.
  • the Combustion vibrations are associated with very high sound pressure amplitudes and a greatly increased heat transfer into the (ring) combustion chamber wall connected, resulting in a reinforced mechanical and thermal loading of the premix burner leads.
  • passive and active methods To eliminate such problems of combustion instability are known as “passive” and “active” methods.
  • the passive methods is characterized by a change of operating parameters (e.g., the air ratio) or the geometry of the premix burner tries to use the self-promotion mechanism disturb and by dissipative measures, such. silencer or obstacles, the occurring sound pressure amplitudes to reduce.
  • operating parameters e.g., the air ratio
  • dissipative measures such. silencer or obstacles, the occurring sound pressure amplitudes to reduce.
  • passive methods are a change of the Pilot gas mass flow, a use of different pilot gas orifices on adjacent burners and the use of Baffels in the fuel system of the premix burner known.
  • Active methods try to build a loop by one or more of the combustion oscillation characterizing Size - for example, pressure and / or power release in the (ring) combustion chamber - processed in a regulator be an actuation signal for one of the self-excited Vibrations exactly opposite or anticyclic Intervention in the oscillating combustion process receive.
  • Active methods are currently fuel side or intervened on the air side and for example by means of a specially adapted valve (a so-called direct drive Valve) the fuel supply to a pilot flame of the premix burner regulated.
  • a specially adapted valve a so-called direct drive Valve
  • actuators of such active systems essentially come valves or piezoelectric or magnetostrictive working components in question.
  • the invention is based on the object, a gas turbine, in particular, a gas turbine in heavy construction, so too to design and operate the aforementioned Combustion instabilities at relatively low cost and easy to handle manner are avoided.
  • the object is according to the invention with an aforementioned Premix burner of a gas turbine solved in which at least a section of the burner and / or at least a section the Vormischgasbrennkanals is movably mounted, an adjustment to move the at least one section the burner and / or the at least a portion of the Premix gas combustion channel is provided and with the adjustment the location of the at least one section of the Burner and / or the location of the at least one section the Vormischgasbrennkanals during operation of the gas turbine is changeable.
  • the invention is further by use of such a premix burner according to the invention in one Gas turbine solved.
  • the invention is with a Process for flame stabilization in a premix burner solved a gas turbine, in which at a (ring) combustion chamber at least one burner and at the fuel gas outlet Premix gas combustion channel are provided, the method the following steps include: Mobile storage of at least a section of the burner and / or at least one Section of Vormischgasbrennkanals, providing an adjustment to move the at least one section the burner and / or the at least a portion of the Premix gas combustion channel and changing the position of at least a portion of the burner and / or the at least one Section of premix gas combustion channel during operation the gas turbine.
  • Premix burner has the adjustment at least one Element for transmitting a force or a moment.
  • the inventive movable portion of Burner and / or the Vormischgasbrennkanals from outside the gas turbine is movable. For the movement is therefore one Remote transmission of forces or moments by specifically for it provided elements useful.
  • the inventive Adjustment at least one element for reduction having an adjustment or a speed per unit time.
  • a reduction can according to the invention provided movable portion of the burner and / or the premix gas combustion channel also with the help of "gross motor” Tools are precisely positioned.
  • the adjusting device also knows at least advantageous an element for slidingly supporting the at least one Section of the burner and / or the at least one section of the premix gas combustion channel.
  • a slide bearing leads in contrast to a roller bearing even at strong changing temperature conditions to a permanently precise Positioning of the invention movable portion of Burner and / or the Vormischgasbrennkanals.
  • a sliding bearing can advantageously a translational plain bearings and / or a rotary plain bearing can be used. In this way, especially in interaction with a gear, a thread and / or a lever especially created varied to varying adjustment become.
  • the adjustment should eventually with at least an actuator provided for externally controlled actuation be.
  • an actuator for example, a hydraulic piston-cylinder arrangement, a hydraulic motor or an electric motor be provided.
  • the use of an actuator is especially advantageous with active flame stabilization, because with the help of the actuator short-term and accurate Adjustments to the geometry of the burner and / or the Vormischgasbrennkanals are possible.
  • Alternative to an actuator The adjusting device according to the invention can also be done manually be operated. Such a manual adjustment can For example, for a passive flame stabilization be cost-effective solution.
  • An intended actuator may be on the outside of the (ring) combustion chamber be held so that he is in front of the influence of high Temperatures protected and easily accessible from the outside.
  • the premix burner according to the invention can be comparatively be easily and inexpensively realized by its burner mounted in total movable and with the adjustment the location of the entire burner is changed.
  • an easy to implement Solution is that the Vormischgasbrennkanal total movably mounted and with the adjustment Location of the entire premix gas combustion channel is changed.
  • Fig. 1 is a first embodiment of a premix burner 10 of a stationary, not further illustrated Gas turbine shown.
  • the premix burner 10 is at a Ring combustion chamber 12 is arranged, the combustion chamber of a housing 14 is substantially enclosed.
  • left end face of the annular combustion chamber 12 are distributed over the circumference of several burners 16 arranged, of which in Fig. 1 one shown in section is.
  • the burner 16 is substantially rod-shaped and has at its the annular combustion chamber 12 end facing a burner nozzle 18.
  • the combustion nozzle 18 is of a Fuel gas outlet 20 surrounded by a gaseous fuel.
  • a substantially circular cylindrical premix gas combustion channel or a burner attachment 22 arranged by means of which the gas flow in the Ring combustion chamber 12 entering the fuel gas and influences so that the burning behavior of the burner 16 are changed can.
  • the premix gas combustion channel 22 is tubular, wherein one end of the tube protrudes into the annular combustion chamber 12 and the other end to the outside of the housing 14 of the annular combustion chamber 12 is guided.
  • the premix gas combustion channel 22 passes through So he is the case 14. He is movably mounted and by means of an adjusting device 24 in its position relative to the housing 14 of the annular combustion chamber 12 changeable.
  • the storage of the Vormischgasbrennkanals 22 is as sliding storage 26 designed a limited, sliding movement in the direction of the longitudinal axis of the rod-shaped burner 16 possible power.
  • the adjusting device 24 comprises a coupling element 28, which is the outer edge of the tubular Vormischgasbrennkanals 22 force-transmitting with a rocker lever 30 and movable connects.
  • the rocker lever 30 is centered pivotally mounted on a bearing 32, which in turn outside is arranged stationary on the housing 14.
  • the rocker arm 30 engages this a cylinder-piston device 34, as the pivot drive the rocker lever 30th move and move the Vormischgasbrennkanal 22 in this meadow can.
  • the displacement of the Vormischgasbrennkanals 22nd is during the ongoing operation of the gas turbine or of the premix burner 10 possible, so that a fast and Situational variation of the geometry at the premix gas combustion channel 22 becomes possible.
  • Fig. 2 is a second embodiment of a premix burner
  • Fig. 10 illustrates that with respect to the burner 16 and the Vormischgasbrennkanals 22 substantially as the premix burner 10 shown in Fig. 1 is constructed.
  • the premix burner 10 shown in FIG. 2 is different constructed.
  • the premix gas combustion channel 22 according to FIG. 2 is with a thread 36 rotatably in the housing 14 of the annular combustion chamber 12 stored, according to the pitch of the threads of the thread 36 when rotating in the direction of the longitudinal axis of the rod-shaped burner 16 shifts.
  • the rotational movement of the premix gas combustion channel is driven 22 via a sprocket 38, a pinion 40, a shaft 42 and an electric motor 44.
  • the ring gear 38 is at the of the Ring combustion chamber 12 opposite end portion of the tubular Premix gas combustion channel 22 is formed.
  • the pinion 40 engages in this sprocket 38 and is rotatably connected to the shaft 42nd connected, which out into another stationary housing section 46 of the premix burner 10 leads.
  • the electric motor 44 is arranged as a rotary drive on the shaft 42 and stationary the further housing portion 46 is supported.
  • Fig. 3 is finally an embodiment of a premix burner 10, in which by means of a single Adjustment device 24 Vormischgasbrennkanäle 22 at several Burners 16 can be adjusted.
  • the premix gas combustion channel 22 again by means of a sliding bearing 26th slidably mounted.
  • a lever mechanism 48 engages the side facing away from the annular combustion chamber 12 edge region the tubular Vormischgasbrennkanals 22 force transmitting at.
  • the lever mechanism 48 can via an adjusting ring 50 are moved, the (similar to an adjustment mechanism at a Vorleitgitter a gas turbine compressor) radially outside and parallel to the annular combustion chamber 12 to all burners 16 is guided around.
  • the adjusting ring 50 is at a Ring bearing 52 mounted and can by a not shown Drive or manually twisted.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
EP03023211A 2003-10-13 2003-10-13 Brûleur à prémélange pour une turbine à gaz Withdrawn EP1524469A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03023211A EP1524469A1 (fr) 2003-10-13 2003-10-13 Brûleur à prémélange pour une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03023211A EP1524469A1 (fr) 2003-10-13 2003-10-13 Brûleur à prémélange pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP1524469A1 true EP1524469A1 (fr) 2005-04-20

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EP03023211A Withdrawn EP1524469A1 (fr) 2003-10-13 2003-10-13 Brûleur à prémélange pour une turbine à gaz

Country Status (1)

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EP (1) EP1524469A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007113130A1 (fr) * 2006-03-30 2007-10-11 Alstom Technology Ltd Systeme de bruleur, de preference dans une chambre de bruleur d'une turbine a gaz
FR2961292A1 (fr) * 2010-06-14 2011-12-16 Snecma Procede pour reduire les instabilites de combustion dans une chambre de combustion ; chambre de combustion de moteur a turbine a gaz selon ce procede
WO2011117533A3 (fr) * 2010-03-23 2012-05-31 Snecma Chambre de combustion a injecteurs decales longitudinalement sur une meme couronne
EP2685161A1 (fr) * 2012-07-10 2014-01-15 Alstom Technology Ltd Agencement de chambre de combustion, en particulier pour turbine à gaz

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2655787A (en) * 1949-11-21 1953-10-20 United Aircraft Corp Gas turbine combustion chamber with variable area primary air inlet
DE2533115A1 (de) * 1975-07-24 1977-02-10 Daimler Benz Ag Brennkammer, insbesondere fuer gasturbinen
US4150539A (en) * 1976-02-05 1979-04-24 Avco Corporation Low pollution combustor
US4350009A (en) * 1977-06-21 1982-09-21 Daimler-Benz Aktiengesellschaft Combustion chamber for a gas turbine
US5211675A (en) * 1991-01-23 1993-05-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Variable volume combustion chamber for a gas turbine engine
US5319923A (en) * 1991-09-23 1994-06-14 General Electric Company Air staged premixed dry low NOx combustor
US5343693A (en) * 1991-09-19 1994-09-06 Hitachi, Ltd. Combustor and method of operating the same

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2655787A (en) * 1949-11-21 1953-10-20 United Aircraft Corp Gas turbine combustion chamber with variable area primary air inlet
DE2533115A1 (de) * 1975-07-24 1977-02-10 Daimler Benz Ag Brennkammer, insbesondere fuer gasturbinen
US4150539A (en) * 1976-02-05 1979-04-24 Avco Corporation Low pollution combustor
US4350009A (en) * 1977-06-21 1982-09-21 Daimler-Benz Aktiengesellschaft Combustion chamber for a gas turbine
US5211675A (en) * 1991-01-23 1993-05-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Variable volume combustion chamber for a gas turbine engine
US5343693A (en) * 1991-09-19 1994-09-06 Hitachi, Ltd. Combustor and method of operating the same
US5319923A (en) * 1991-09-23 1994-06-14 General Electric Company Air staged premixed dry low NOx combustor

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007113130A1 (fr) * 2006-03-30 2007-10-11 Alstom Technology Ltd Systeme de bruleur, de preference dans une chambre de bruleur d'une turbine a gaz
WO2011117533A3 (fr) * 2010-03-23 2012-05-31 Snecma Chambre de combustion a injecteurs decales longitudinalement sur une meme couronne
FR2961292A1 (fr) * 2010-06-14 2011-12-16 Snecma Procede pour reduire les instabilites de combustion dans une chambre de combustion ; chambre de combustion de moteur a turbine a gaz selon ce procede
EP2685161A1 (fr) * 2012-07-10 2014-01-15 Alstom Technology Ltd Agencement de chambre de combustion, en particulier pour turbine à gaz
CN103542403A (zh) * 2012-07-10 2014-01-29 阿尔斯通技术有限公司 尤其用于燃气涡轮的燃烧器布置
JP2014016150A (ja) * 2012-07-10 2014-01-30 Alstom Technology Ltd 特にガスタービン用の燃焼器配列
CN103542403B (zh) * 2012-07-10 2016-09-28 通用电器技术有限公司 燃烧器
US9933163B2 (en) 2012-07-10 2018-04-03 Ansaldo Energia Switzerland AG Combustor arrangement with slidable multi-cone premix burner

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