EP1096201A1 - Brûleur - Google Patents

Brûleur Download PDF

Info

Publication number
EP1096201A1
EP1096201A1 EP99121577A EP99121577A EP1096201A1 EP 1096201 A1 EP1096201 A1 EP 1096201A1 EP 99121577 A EP99121577 A EP 99121577A EP 99121577 A EP99121577 A EP 99121577A EP 1096201 A1 EP1096201 A1 EP 1096201A1
Authority
EP
European Patent Office
Prior art keywords
swirl
combustion air
burner
combustion
blades
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Withdrawn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
EP99121577A
Other languages
German (de)
English (en)
Inventor
Olaf Hein
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 EP99121577A priority Critical patent/EP1096201A1/fr
Priority to EP00972775A priority patent/EP1224423B1/fr
Priority to JP2001534984A priority patent/JP4567266B2/ja
Priority to CNB008151075A priority patent/CN1143980C/zh
Priority to DE50007809T priority patent/DE50007809D1/de
Priority to PCT/EP2000/010167 priority patent/WO2001033138A1/fr
Publication of EP1096201A1 publication Critical patent/EP1096201A1/fr
Priority to US10/133,926 priority patent/US6688109B2/en
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • 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
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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 burner with a combustion air supply duct.
  • the Air intake silencer consists of one of an impermeable Wall enclosed flow line with Subsonic speed of a gaseous medium is flowed through.
  • This Device is in front of one in the flow direction of the medium arranged sound-transmitting noise source and serves the Suppression of airborne noise emissions against the direction of flow.
  • the device has a laval nozzle-like Narrowing of the flow line. Through this laval nozzle-like Narrowing becomes the velocity of the gaseous Medium accelerated to the speed of sound. So that will built a reflection barrier for airborne sound.
  • combustion vibrations In combustion systems, it can develop combustion vibrations come. Such combustion vibrations are described in the article "Combustion-Driven-Oscillations in Industry "by Abbott A. Putnam, American Elsevier, New York 1971. According to the Rayleigh criterion, one is built Combustion vibration with a periodic supply of Heat up an amount of air in a combustion chamber if this Heat supply as a periodic release of combustion power in phase with a natural vibration of the air in the Combustion chamber takes place. Accordingly, the combustion vibration through an anti-phase power release be suppressed. Such combustion vibrations can considerable noise pollution and even mechanical Damage to components of the combustion device to lead.
  • Pulsations in supply rate stated that the Combustion vibration to an air or fuel supply can be coupled.
  • Pulsations in the delivery systems are suggested to bring about great pressure loss in the delivery systems to build a barrier to reflection. But it will be fine noted that such a pressure loss usually is unacceptable.
  • the object of the invention is to provide a burner in which a combustion zone into which the burner opens, from one Supply of combustion air for the burner is decoupled in terms of flow acoustics, with this decoupling at most an acceptable additional pressure loss arises in the combustion air.
  • this object is achieved by a burner with a combustion air duct in which one of a number Swirl generator formed by swirl generator elements arranged in this way is that by the swirl generator the average passage speed of those passed through the swirl generator Combustion air to a Mach number of at least 0.4, in particular at least 0.6, is increased.
  • the average speed of passage is the over averaged a duct cross section of the combustion air duct Speed.
  • Swirl generators are often used in a burner to the combustion air entering the combustion chamber to give a twist which is the combustion flame stabilized.
  • a reflection barrier of at least 0.4 is created via the swirl generator built for sound waves. This will make the Propagation of combustion vibrations in the supply system weakened or even prevented for combustion air.
  • About the construction of the reflection barrier using the Swirl generator can cause a pressure loss in the combustion air be kept small.
  • the acoustic decoupling thus has a slightly negative effect on the Efficiency of a combustion device in which the Burner is integrated.
  • a swirl vane ring in the combustion air duct from swirl blades to generate a swirl in the Combustion air arranged.
  • the swirl generator is further preferred formed by the swirl vane ring. So instead to provide additional swirl generators for acoustic decoupling, is an already existing swirl vane ring as acoustically decoupling swirl generator.
  • an already existing swirl vane ring as acoustically decoupling swirl generator.
  • the Swirl generator as a swirl vane ring thus has both Advantage that it is a necessary means of production anyway a swirl stabilizing the combustion provided will, as well as a favorable on efficiency effective pressure recovery in the combustion air becomes.
  • the swirl vane ring preferably has first and second Scoops up along the circumferential direction of the swirl vane ring alternating successively, the second blades against a flow direction of the Combustion air offset from the first blades are.
  • the first blades preferably have one first maximum profile thickness and the second blades one second maximum profile thickness, the first maximum Profile thickness is greater than the second maximum profile thickness.
  • the first blades have a first chord length and second blades a second chord length. Preferably the first chord length is smaller than the second Chord length.
  • the Shoveling one of the partial rings preferably longer and thinner than the blades of the other partial ring, namely, are preferred the blades of that part of the ring longer and thinner, which is arranged in the direction of flow in front of the other partial ring is.
  • the two functions the swirl vane ring are optimized, d. H. both the Function of the swirl generation as well as the function of the acoustic Decoupling can be done by appropriate dimensioning and matching the partial wreaths to each other in sufficient Dimensions are met.
  • this structure is simple Possibility of a swirl vane ring in a burner like this to retrofit that he subsequently the desired acoustic Decoupling enabled.
  • the combustion air duct is preferably annular.
  • Fuel is preferably in the combustion air duct inlet, which is before combustion with the combustion air intensely mixed.
  • The is more preferred Fuel from at least some of the swirl generator elements openable.
  • Through the intensive mixing of the fuel with the combustion air before the combustion (premix burner), will reduce nitrogen oxide emissions reached. This is done by leveling the flame temperature due to the good mixing, since the Nitrogen oxide emission exponentially with the flame temperature increases.
  • Another advantage of acoustic decoupling an additional mixing results from the swirl generator of fuel and combustion air because through the pronounced acceleration of the combustion air and the subsequent zone of pressure recovery additional swirls in the combustion air for a further improvement the mixing of combustion air and fuel to lead.
  • the swirl generator can also be dimensioned in this way be that on part of the pressure recovery is dispensed with in favor of increased turbulence improved mixing.
  • the burner preferably has an additional pilot burner on, through which a combustion of the combustion air duct escaping fuel-combustion air mixture is stabilized.
  • the pilot burner work as Diffusion burner, d. H.
  • Fuel and combustion air of the Pilot burners are only mixed at the point of combustion, so the burner is also referred to as a hybrid burner, in which both premix combustion and diffusion combustion he follows.
  • the burner is a gas turbine burner educated. Especially when it comes to high performance implementation Gas turbines can have very large combustion vibrations Amplitudes and possibly considerable damage effects occur. The flow acoustic decoupling to the combustion air supply system is particularly important here. this applies especially for stationary gas turbines.
  • FIG. 1 shows a gas turbine 301 in a longitudinal section. Arranged one behind the other along a turbine axis 302 are a compressor 303, a combustor 305 and a Turbine part 307.
  • the combustion chamber 305 opens into the burner 100. This comprises an annular duct-shaped combustion air duct 104 and a central one, from the combustion air duct 104 surrounding pilot burner 106.
  • the pilot burner 106 is as a diffusion burner executed in the fuel 114 and Compressor air 112 mixed in a combustion zone 311 and be burned.
  • fuel 114 of the combustion air 112 admixed from the compressor 303.
  • the combustion air 112 initially mixes intimately with the Fuel 114 before it is also in the combustion zone 311 burns within the combustion chamber 305. This so-called Premixed combustion is achieved through the diffusion combustion of the Pilot burner 106 stabilized.
  • burning in the Combustion chamber 305 generates hot exhaust gas 315, which the Turbine part 307 is fed.
  • Blading shown in turbine part 307 is the energy one of the hot exhaust gases 315 in rotational energy is not closer shown turbine shaft implemented.
  • Fluctuations in the combustion flame 313 result in Propagation of sound waves within the combustion chamber 305, that are reflected from the combustion chamber walls and in place the combustion 311 in turn fluctuations in the flame 313 cause. This interaction can cause a certain combustion chamber vibration at certain frequencies of the fluctuations build up in the combustion chamber 305 that too significant noise or even damage of components of the gas turbine 301 can lead. These combustion vibrations also spread through the combustion air duct 104 out. Through the combustion air duct 104 thus an additional volume to the combustion chamber 305 coupled, through which the formation of combustion chamber vibrations can also be favored. In addition Components upstream of the combustion chamber 305 also below Exposed to damaging vibrations.
  • the combustion air duct 104 flow acoustic to decouple from the combustion chamber 305.
  • a simple and acceptable from the pressure loss Possibility of acoustic decoupling of the combustion chamber 305 and combustion air duct 104 by means of a 2 shows burner 100.
  • FIG. 2 shows partially cut open and one in perspective burner 100 directed along a focal axis 98 an inner wall 101 and an outer wall 102 is an annular channel Combustion air duct 104 is formed. This encloses a centrally arranged, not shown in detail Pilot burner 106.
  • a swirl generator 109 designed as a swirl vane ring arranged. This is made of swirl blades Swirl generator elements 108 are formed.
  • the swirl blades 108 are in their position by adjusting screws 110 in the Outer wall 102 adjustable.
  • the swirl vane ring 109 is thereby alternating along its circumferential direction U. successive, different swirl blades 108 educated.
  • a first swirl vane 108B follows a second swirl vane 108A each.
  • the first swirl blades 108B are opposite the second swirl blades 108a staggered and both shorter and thicker. This is explained in more detail below with reference to FIG 3. Out some, preferably all of the swirl blades 108 is by means of one running inside the swirl vane 108, here invisible fuel channel fuel 114 over Openings, especially around the blade leading edge, let into the combustion air duct 104. By the Combustion air duct 104 flows combustion air 112. This mixes intensively with the fuel 114 Dimensioning of the swirl blades 108 becomes the combustion air 112 accelerated to a Mach number above 0.4. This creates a reflection barrier for sound waves built up.
  • FIG. 3 shows three of the swirl blades 108 in a cross section namely, second swirl blades 108A and an intermediate one first swirl vane 108B.
  • the first swirl vane 108B has a leading edge point 200B, a trailing edge point 202B, a skeletal line 204B, a maximum Profile thickness 206B and an adjustment engagement 208B.
  • each second swirl vane 108A has one Blade leading edge point 208A, a blade trailing edge point 202A, a skeleton line 204A, a maximum profile thickness 206A and an adjustment engagement 208A.
  • Combustion air 112 flows along the flow direction 210 between the first Swirl vane 108B and one of the second swirl vanes 108A through it.
  • the first is along this flow direction 210 Swirl vane 108B opposite second swirl vane 108A set back so that there is a distance L1 between the Tangents to the respective blade leading edge points 200B, 200A results.
  • a passage cross section F1 for the between Combustion air 112 flowing through the swirl vanes 108 shrinks down to a maximum narrowing caused by a minimum distance L4 between the first swirl vane 108B and the second swirl vane 108A. After this maximum constriction, the passage cross section increases F2 again and so moderately that it is not to a stall and thus to pressure losses due to comes from vortex formation. This will result in a high pressure recovery ensured in the combustion air 112.
  • the Blade trailing edge points 202B, 202A 112 are indicated by the Distance L3 spaced apart.
  • the first swirl blades 108B both have a greater maximum profile thickness than 206B also a shorter chord 204B compared to the maximum profile thicknesses 206A or 204A second swirl blades 108A.
  • This alternating Vane design in the swirl vane ring 109 enables both the setting of a sufficiently high swirl Stabilization of a combustion as well as desired acoustic decoupling effect by accelerating the combustion air 112 and then pressure recovery.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Air Supply (AREA)
EP99121577A 1999-10-29 1999-10-29 Brûleur Withdrawn EP1096201A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP99121577A EP1096201A1 (fr) 1999-10-29 1999-10-29 Brûleur
EP00972775A EP1224423B1 (fr) 1999-10-29 2000-10-16 Bruleur
JP2001534984A JP4567266B2 (ja) 1999-10-29 2000-10-16 バーナ
CNB008151075A CN1143980C (zh) 1999-10-29 2000-10-16 燃烧器
DE50007809T DE50007809D1 (en) 1999-10-29 2000-10-16 Brenner
PCT/EP2000/010167 WO2001033138A1 (fr) 1999-10-29 2000-10-16 Bruleur
US10/133,926 US6688109B2 (en) 1999-10-29 2002-04-26 Turbine engine burner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99121577A EP1096201A1 (fr) 1999-10-29 1999-10-29 Brûleur

Publications (1)

Publication Number Publication Date
EP1096201A1 true EP1096201A1 (fr) 2001-05-02

Family

ID=8239298

Family Applications (2)

Application Number Title Priority Date Filing Date
EP99121577A Withdrawn EP1096201A1 (fr) 1999-10-29 1999-10-29 Brûleur
EP00972775A Expired - Lifetime EP1224423B1 (fr) 1999-10-29 2000-10-16 Bruleur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP00972775A Expired - Lifetime EP1224423B1 (fr) 1999-10-29 2000-10-16 Bruleur

Country Status (6)

Country Link
US (1) US6688109B2 (fr)
EP (2) EP1096201A1 (fr)
JP (1) JP4567266B2 (fr)
CN (1) CN1143980C (fr)
DE (1) DE50007809D1 (fr)
WO (1) WO2001033138A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005093326A2 (fr) * 2004-03-29 2005-10-06 Alstom Technology Ltd Chambre a combustion de turbine a gaz et procede pour la faire fonctionner
EP1795807A2 (fr) * 2005-12-08 2007-06-13 General Electric Company Ensemble tourbillonnaire
WO2008019997A1 (fr) * 2006-08-16 2008-02-21 Siemens Aktiengesellschaft Passage de coupelle rotative et brûleur pour moteur à turbine à gaz
CN101153558A (zh) * 2006-09-29 2008-04-02 通用电气公司 预混设备、包括预混设备的燃气涡轮机及使用方法
WO2009087050A2 (fr) 2008-01-08 2009-07-16 Ln 2 S.R.L. A Socio Unico Dispositif de mélange d'air et de gaz, destiné en particulier à des appareils brûleurs à prémélange
EP2796788A1 (fr) * 2013-04-24 2014-10-29 Alstom Technology Ltd Générateur de tourbillon
EP3236157A1 (fr) * 2016-04-22 2017-10-25 Siemens Aktiengesellschaft Générateur de tourbillonnement pour mélanger un combustible avec de l'air dans un moteur à combustion

Families Citing this family (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4161493B2 (ja) * 1999-12-10 2008-10-08 ソニー株式会社 エッチング方法およびマイクロミラーの製造方法
EP1499800B1 (fr) 2002-04-26 2011-06-29 Rolls-Royce Corporation Module de premelange de combustible pour chambre de combustion de turbine a gaz
DE10233161B4 (de) * 2002-07-22 2012-01-05 Alstom Technology Ltd. Brenner und Pilotbrenner
EP1394471A1 (fr) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brûleur
DE10348604A1 (de) * 2003-10-20 2005-07-28 Rolls-Royce Deutschland Ltd & Co Kg Kraftstoffeinspritzdüse mit filmartiger Kraftstoffplatzierung
DE102004059882A1 (de) * 2004-12-10 2006-06-22 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner mit integriertem Stützbrenner
WO2007036964A1 (fr) * 2005-09-30 2007-04-05 Ansaldo Energia S.P.A. Procédé d’activation d’une turbine à gaz équipée d’un brûleur à gaz, et dispositif de tourbillonnement axial pour ledit brûleur
US8769960B2 (en) * 2005-10-21 2014-07-08 Rolls-Royce Canada, Ltd Gas turbine engine mixing duct and method to start the engine
EP1821035A1 (fr) * 2006-02-15 2007-08-22 Siemens Aktiengesellschaft Brûleur de turbine à gaz et procédé pour mélanger le carburant et l'air dans une zone de tourbillonage d'un brûleur de turbine à gaz
US7631500B2 (en) * 2006-09-29 2009-12-15 General Electric Company Methods and apparatus to facilitate decreasing combustor acoustics
EP1918638A1 (fr) * 2006-10-25 2008-05-07 Siemens AG Brûleur, en particulier pour une turbine à gaz
EP1921376A1 (fr) * 2006-11-08 2008-05-14 Siemens Aktiengesellschaft Sistème d'injection de carburant
GB2444737B (en) * 2006-12-13 2009-03-04 Siemens Ag Improvements in or relating to burners for a gas turbine engine
US20080276622A1 (en) * 2007-05-07 2008-11-13 Thomas Edward Johnson Fuel nozzle and method of fabricating the same
DE102007043626A1 (de) 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
US20090255118A1 (en) * 2008-04-11 2009-10-15 General Electric Company Method of manufacturing mixers
EP2154432A1 (fr) * 2008-08-05 2010-02-17 Siemens Aktiengesellschaft Appareil de tourbillonnement pour mélanger du carburant et de l'air
US8291705B2 (en) * 2008-08-13 2012-10-23 General Electric Company Ultra low injection angle fuel holes in a combustor fuel nozzle
US8113002B2 (en) * 2008-10-17 2012-02-14 General Electric Company Combustor burner vanelets
US8104286B2 (en) * 2009-01-07 2012-01-31 General Electric Company Methods and systems to enhance flame holding in a gas turbine engine
US20100180599A1 (en) * 2009-01-21 2010-07-22 Thomas Stephen R Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle
EP2246617B1 (fr) * 2009-04-29 2017-04-19 Siemens Aktiengesellschaft Brûleur pour moteur de turbine à gaz
US8172510B2 (en) * 2009-05-04 2012-05-08 Hamilton Sundstrand Corporation Radial compressor of asymmetric cyclic sector with coupled blades tuned at anti-nodes
US8172511B2 (en) * 2009-05-04 2012-05-08 Hamilton Sunstrand Corporation Radial compressor with blades decoupled and tuned at anti-nodes
US20110067377A1 (en) * 2009-09-18 2011-03-24 General Electric Company Gas turbine combustion dynamics control system
JP2011099654A (ja) * 2009-11-09 2011-05-19 Mitsubishi Heavy Ind Ltd ガスタービン用燃焼バーナ
US9435537B2 (en) * 2010-11-30 2016-09-06 General Electric Company System and method for premixer wake and vortex filling for enhanced flame-holding resistance
US20130067923A1 (en) * 2011-09-20 2013-03-21 General Electric Company Combustor and method for conditioning flow through a combustor
CN105737203B (zh) * 2016-03-16 2018-11-06 内蒙古中科朴石燃气轮机有限公司 一种旋流器及采用其的预混燃烧器
US20180058696A1 (en) * 2016-08-23 2018-03-01 General Electric Company Fuel-air mixer assembly for use in a combustor of a turbine engine
KR102096580B1 (ko) * 2019-04-01 2020-04-03 두산중공업 주식회사 예혼합 균일성이 향상된 연소기 노즐 및 이를 구비하는 가스터빈용 연소기
EA039073B1 (ru) * 2020-09-07 2021-11-30 Некоммерческое Акционерное Общество "Алматинский Университет Энергетики И Связи Имени Гумарбека Даукеева" Двухъярусная горелка
CN113864823B (zh) * 2021-11-09 2022-08-26 滨州学院 涡轮发动机循环加热多级燃烧系统
CN115325564B (zh) * 2022-07-21 2023-06-30 北京航空航天大学 一种结合气动导流燃烧振荡抑制方法和装置

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0122526A1 (fr) * 1983-04-13 1984-10-24 BBC Aktiengesellschaft Brown, Boveri & Cie. Injecteur de combustible pour la chambre de combustion d'une turbine à gaz
US4483138A (en) * 1981-11-07 1984-11-20 Rolls-Royce Limited Gas fuel injector for wide range of calorific values
DE3836446A1 (de) * 1988-10-26 1990-05-03 Proizv Ob Nevskij Z Im V I Verfahren fuer die luftzufuhr zur brennzone einer brennkammer und brennkammer zur durchfuehrung dieses verfahrens
EP0572202A1 (fr) * 1992-05-27 1993-12-01 General Electric Company Procédé et dispositif pour réduire les oscillations de concentration air-carburant dans une chambre de combustion
DE4430697C1 (de) 1994-08-30 1995-09-14 Freudenberg Carl Fa Zuluftschalldämpfer
US5451160A (en) * 1991-04-25 1995-09-19 Siemens Aktiengesellschaft Burner configuration, particularly for gas turbines, for the low-pollutant combustion of coal gas and other fuels
US5558515A (en) * 1994-04-02 1996-09-24 Abb Management Ag Premixing burner
US5927076A (en) * 1996-10-22 1999-07-27 Westinghouse Electric Corporation Multiple venturi ultra-low nox combustor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3570242A (en) * 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
JPS6122127A (ja) * 1984-07-10 1986-01-30 Hitachi Ltd ガスタ−ビン燃焼器
DE4417536A1 (de) * 1994-05-19 1995-11-23 Abb Management Ag Verfahren zum Betrieb einer Brennkammer
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
JP3494753B2 (ja) * 1995-04-26 2004-02-09 株式会社日立製作所 ガスタービン燃焼器
DE59903398D1 (de) * 1998-03-20 2002-12-19 Siemens Ag Gasturbinenbrenner
JP2002531805A (ja) * 1998-12-08 2002-09-24 シーメンス アクチエンゲゼルシヤフト 燃焼装置および燃焼方法

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4483138A (en) * 1981-11-07 1984-11-20 Rolls-Royce Limited Gas fuel injector for wide range of calorific values
EP0122526A1 (fr) * 1983-04-13 1984-10-24 BBC Aktiengesellschaft Brown, Boveri & Cie. Injecteur de combustible pour la chambre de combustion d'une turbine à gaz
DE3836446A1 (de) * 1988-10-26 1990-05-03 Proizv Ob Nevskij Z Im V I Verfahren fuer die luftzufuhr zur brennzone einer brennkammer und brennkammer zur durchfuehrung dieses verfahrens
US5451160A (en) * 1991-04-25 1995-09-19 Siemens Aktiengesellschaft Burner configuration, particularly for gas turbines, for the low-pollutant combustion of coal gas and other fuels
EP0572202A1 (fr) * 1992-05-27 1993-12-01 General Electric Company Procédé et dispositif pour réduire les oscillations de concentration air-carburant dans une chambre de combustion
US5558515A (en) * 1994-04-02 1996-09-24 Abb Management Ag Premixing burner
DE4430697C1 (de) 1994-08-30 1995-09-14 Freudenberg Carl Fa Zuluftschalldämpfer
US5927076A (en) * 1996-10-22 1999-07-27 Westinghouse Electric Corporation Multiple venturi ultra-low nox combustor

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
"Gaswärme International, band 41, heft 1", January 1992, article D. SCHRÖDER: "Massnahmen zur Vermeidung von Verbrennungsschwingungen - Kennzahl zur Stömungsakustischen Entkopplung am Brenner"
ABBOTT A. PUTNAM: "Combustion-Driven-Oscillations in Industry", 1971, AMERICAN ELSEVIER, NEW YORK
CHRISTIAN FABER: "Berechnung der Schallausbreitung in durchströmten Kanälen von Turbomaschinen unter besonderer Berücksichtigung der Auslegung von Drehonschaltern", 1993, VERLAG SHAKER, AACHEN

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005093326A3 (fr) * 2004-03-29 2006-02-09 Alstom Technology Ltd Chambre a combustion de turbine a gaz et procede pour la faire fonctionner
WO2005093326A2 (fr) * 2004-03-29 2005-10-06 Alstom Technology Ltd Chambre a combustion de turbine a gaz et procede pour la faire fonctionner
EP1795807A2 (fr) * 2005-12-08 2007-06-13 General Electric Company Ensemble tourbillonnaire
EP1795807A3 (fr) * 2005-12-08 2009-01-28 General Electric Company Ensemble tourbillonnaire
US8181464B2 (en) 2006-08-16 2012-05-22 Siemens Aktiengesellschaft Swirler with concentric fuel and air tubes for a gas turbine engine
WO2008019997A1 (fr) * 2006-08-16 2008-02-21 Siemens Aktiengesellschaft Passage de coupelle rotative et brûleur pour moteur à turbine à gaz
EP1892469A1 (fr) * 2006-08-16 2008-02-27 Siemens Aktiengesellschaft Passage de tourbillonneur et brûleur pour une turbine à gaz
CN101153558A (zh) * 2006-09-29 2008-04-02 通用电气公司 预混设备、包括预混设备的燃气涡轮机及使用方法
EP1916481A2 (fr) * 2006-09-29 2008-04-30 General Electric Company Appareil de prémélange, gas turbine comprenant ledit appareil de prémélange, et méthode d'utilisation
EP1916481A3 (fr) * 2006-09-29 2012-11-21 General Electric Company Appareil de prémélange, gas turbine comprenant ledit appareil de prémélange, et méthode d'utilisation
WO2009087050A2 (fr) 2008-01-08 2009-07-16 Ln 2 S.R.L. A Socio Unico Dispositif de mélange d'air et de gaz, destiné en particulier à des appareils brûleurs à prémélange
WO2009087050A3 (fr) * 2008-01-08 2010-05-20 Ln 2 S.R.L. A Socio Unico Dispositif de mélange d'air et de gaz, destiné en particulier à des appareils brûleurs à prémélange
EP2796788A1 (fr) * 2013-04-24 2014-10-29 Alstom Technology Ltd Générateur de tourbillon
EP3236157A1 (fr) * 2016-04-22 2017-10-25 Siemens Aktiengesellschaft Générateur de tourbillonnement pour mélanger un combustible avec de l'air dans un moteur à combustion
WO2017182658A1 (fr) * 2016-04-22 2017-10-26 Siemens Aktiengesellschaft Coupelle de turbulence pour le mélange de carburant avec l'air dans un moteur à combustion
RU2716951C1 (ru) * 2016-04-22 2020-03-17 Сименс Акциенгезелльшафт Завихритель для смешивания топлива с воздухом в двигателе сгорания
US10876731B2 (en) 2016-04-22 2020-12-29 Siemens Aktiengesellschaft Swirler for mixing fuel with air in a combustion engine

Also Published As

Publication number Publication date
CN1384908A (zh) 2002-12-11
JP2003513223A (ja) 2003-04-08
WO2001033138A1 (fr) 2001-05-10
US20020174656A1 (en) 2002-11-28
CN1143980C (zh) 2004-03-31
EP1224423B1 (fr) 2004-09-15
DE50007809D1 (en) 2004-10-21
JP4567266B2 (ja) 2010-10-20
US6688109B2 (en) 2004-02-10
EP1224423A1 (fr) 2002-07-24

Similar Documents

Publication Publication Date Title
EP1224423B1 (fr) Bruleur
DE102009003639B4 (de) Verfahren und Systeme zur Verminderung von Verbrennungsdynamik
DE69128725T2 (de) Verfahren und einrichtung um die strömung in gasturbinenmotoren zu verbessern
EP1343956B1 (fr) Ensemble soufflante a canal de derivation attenuateur de bruit
DE4316475C2 (de) Gasturbinen-Brennkammer
EP1517022A2 (fr) Méthode et système de réduction de bruit d'un turboréacteur
CN110006068B (zh) 用于燃气涡轮发动机燃烧器的燃料喷嘴
CH702575B1 (de) Kraftstoffdüse und Gasturbinenmotor.
EP1048898B1 (fr) Brûleur
DE60211877T2 (de) Ondulierte mischdüse für strahltriebwerke
CH701293B1 (de) Brennstoffdüse mit einer Verwirbleranordnung und mehreren Leitschaufeln sowie Gasturbinentriebwerk.
JPH11264345A (ja) 交互のローブ状のミキサ／エゼクタ構想サプレッサ
DE102015219556A1 (de) Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
CH701543B1 (de) Brenner zur Verwendung in einer Gasturbine sowie Gasturbine.
CH708946A2 (de) Vormischeranordnung zur Vermischung von Luft und Brennstoff zur Verbrennung.
CH709266A2 (de) Turbinenschaufel und Verfahren zum Auswuchten eines Spitzendeckbandes einer Turbinenschaufel und Gasturbine.
DE19850732A1 (de) Axialturbine
US3364678A (en) Means for stabilizing fluid flow in diffuser-combustor systems in axial flow gas turbine engines
EP1137899B1 (fr) Dispositif de combustion et procede de combustion d'un combustible
DE112015003797B4 (de) Gasturbine
EP1642065B1 (fr) Ensemble de brûleur pour une turbine à gaz et turbine à gaz
US11834997B2 (en) Face sheet of acoustic liner having streamlined holes with elongated edges
EP2147204B1 (fr) Groupe turbines à gaz et procédé de commande d'un groupe turbines à gaz
JP4168695B2 (ja) ローブミキサ
WO2010136300A2 (fr) Brûleur et procédé pour réduire des oscillations de flammes auto-induites dans un brûleur

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

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

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20011103