EP2587158A1 - Chambre de combustion pour une turbine à gaz et agencement de brûleur - Google Patents

Chambre de combustion pour une turbine à gaz et agencement de brûleur Download PDF

Info

Publication number
EP2587158A1
EP2587158A1 EP11187285.9A EP11187285A EP2587158A1 EP 2587158 A1 EP2587158 A1 EP 2587158A1 EP 11187285 A EP11187285 A EP 11187285A EP 2587158 A1 EP2587158 A1 EP 2587158A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
fuel
combustion
stepped
premix passage
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Withdrawn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
EP11187285.9A
Other languages
German (de)
English (en)
Inventor
Christian Beck
Olga Deiss
Werner Dr. Krebs
Bernhard Wegner
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 EP11187285.9A priority Critical patent/EP2587158A1/fr
Priority to CN201280065621.7A priority patent/CN104024737B/zh
Priority to PCT/EP2012/070783 priority patent/WO2013064383A1/fr
Priority to US14/355,467 priority patent/US20140260265A1/en
Priority to EP12780155.3A priority patent/EP2773907A1/fr
Publication of EP2587158A1 publication Critical patent/EP2587158A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/28—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
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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 chamber for a gas turbine having at least one combustion zone and at least one burner arrangement for combustion of a fuel / air mixture, wherein the burner arrangement comprises at least one premix passage opening into the combustion zone for providing a fuel / air mixture, and into the premix passage from the burner assembly included air supply and at least one fuel supply opens.
  • the invention also relates to a gas turbine with such a combustion chamber and to a burner assembly.
  • Known gas turbines comprise, in addition to an initially mentioned combustion chamber, a compressor and a turbine.
  • the compressor compresses the gas supplied to the gas turbine, a portion of this air is used to burn fuel in the combustion chamber and a part is used to cool the gas turbine and / or the combustion gases.
  • the hot gases provided by the combustion process in the combustion chamber are introduced into the turbine from the combustion chamber, where they relax and cool, causing turbine blades to rotate under the action of work.
  • the gas turbine drives a work machine.
  • the work machine may be, for example, a generator.
  • the fuel / air mixture provided by the at least one burner assembly is premixed in the at least one premix passage to then be ignited after flowing into the combustion zone.
  • the premixing of the fuel with the air reduces the pollutant emissions produced during the combustion, in contrast to the previously customary direct injection of the fuel into the combustion zone.
  • a disadvantage of the premix of the fuel is much more susceptible to the formation of combustion chamber pressure fluctuations. If there are pressure fluctuations in the combustion zone, there are also concentration fluctuations in the fuel / air mixture in the premix passage, which lead to heat release fluctuations during combustion. These thermoacoustic instabilities in turn increase the combustion chamber pressure fluctuations, wherein there are preferred frequencies in the arrangement for these alsschaukelnden combustion chamber pressure fluctuations.
  • the concentration variations in the fuel / air mixture may also be referred to as air frequency fluctuations.
  • the air frequency fluctuations result from different acoustic resistances of the air supply and fuel supply.
  • known gas turbines comprise resonators arranged in the housing. Since the resonators are directly adjacent to the combustion zone and also interrupt a heat shield arrangement in the housing and therefore have to be cooled, such a design of the combustion chamber is expensive.
  • An alternative embodiment of a known combustion chamber provides for suppression of such combustion chamber pressure fluctuations that the fuel nozzles opening into the premix passage are distributed along the premix passage in the axial direction, so that mixing zones with different delay times are formed in the premix passage. This staged design of the fuel supply makes it possible to mitigate the fluctuations in concentration caused by the combustion chamber pressure fluctuation in the fuel injected by the fuel supply.
  • the fuel nozzles may also be referred to with outlet openings of the fuel supply.
  • the object of the invention is to provide a combustion chamber of the aforementioned type and a gas turbine with such a combustion chamber and a burner arrangement comprising such a combustion chamber, which enables a particularly effective damping of combustion chamber pressure fluctuations.
  • the object is achieved according to the invention in a combustion chamber of the type mentioned above in that the air supply is stepped, so that different delay times can be assigned to the outlet opening of the stepped air supply opening into the premix passage.
  • the stepped air supply comprises outlet openings which open into the premix passage and to which different delay times can be assigned.
  • the stepped air supply may further comprise further outlet openings, which redundant delay times can be assigned.
  • the delay time can also be referred to as convective time delay. It is determined by the time it takes for a fluid element entering the premix passage to travel to the combustion zone to get.
  • the outlet openings can also be referred to with outlet openings.
  • the burner assembly may include a pilot burner having a premix passage with a pilot burner lance centrally disposed therein, the pilot burner lance connected to a fuel supply and including fuel nozzles.
  • the premix passage of the pilot burner opens an air supply.
  • a plurality of main mixers included in the burner assembly can be arranged.
  • Each of the main mixers may comprise a premix passage comprised of a cylindrical housing, into which an air feed opens, and in which is axially arranged a fuel nozzle lance connected to a fuel supply.
  • the lance can be supported, for example via swirl blades on the housing.
  • at least one of the premix passages in the exemplified burner arrangement comprises a stepped air feed.
  • the air supply of the main mixer can be formed stepped by the swirl blades form in the premix passage opening air outlet openings, which different delay times can be assigned.
  • These can preferably be selected such that, at least in the frequency range of a preferred combustion chamber pressure fluctuation, density fluctuations in the supplied air caused by these are canceled or reduced by means of the different delay times of the air outlet openings.
  • An advantageous development of the invention can provide that in addition to the stepped air supply formed in the premix passage and can be acted upon with gaseous fuel supply also formed stepwise.
  • the gaseous fuel also has a high compressibility compared to air, can be through the additional grading of gaseous fuel acted upon fuel supply by combustion chamber pressure fluctuations caused fluctuations in the concentration and density of the flowing from the Vormischpassage into the combustion zone fuel / air mixture even more effectively attenuate.
  • the premix passage comprises more than one fuel feed which can be acted upon by gaseous fuel, one or more of these fuel feeds which can be acted upon by gaseous fuel can be designed in a stepped manner.
  • delay times can be assigned to the outlet openings of the stepped feed, wherein for a minimum delay time ⁇ min and a maximum delay time ⁇ max with respect to a suppressible combustion chamber pressure fluctuation of the frequency f: ⁇ max - ⁇ min > 1 / f.
  • the condition ensures that, at least in the frequency range of the combustion chamber pressure fluctuation to be suppressed, density fluctuations caused thereby in the fluid supplied by the stepped supply are effectively attenuated.
  • the stepped feeder is the stepped air supply. If further feeds leading into the premix passage are formed in a stepped manner, the condition can also apply to these feeds.
  • the minimum and maximum delay time specified in the condition refers to the shortest or the longest of the delay times associated with the outlet ports of a feeder.
  • outlet ports of the stepped supply opening into the premix passage are arranged such that density fluctuations caused by at least one preferred combustion chamber pressure fluctuation of the frequency f 'in the fluid supplied through the outlet openings in the premix passage due to the outlet openings assigned different delay times superimpose such that they essentially cancel each other out.
  • the burner arrangement is arranged in the region of a second axial stage with at least one premix passage opening into the combustion zone, the combustion zone following downstream of a first combustion zone with a first burner arrangement.
  • a second axial stage By means of a second axial stage, the heat release over the entire available combustion chamber can be further distributed, so that the tendency of the combustion system to thermoacoustic instabilities is further reduced.
  • a stepped air supply to at least one premix passage of the burner arrangement of the second axial stage is particularly easy to implement in terms of apparatus.
  • a preferred embodiment of the invention can provide that the burner arrangement comprises a fuel distributor ring disposed outside a combustion chamber housing and a multiplicity of premix passage, wherein the premix passages open into the combustion chamber with their one end into the combustion chamber and with at least one fuel feed branching off from the fuel distributor ring correspond, wherein at least along one of the Vormischpassagen outlet openings of a stepped air supply are arranged distributed.
  • the premixing passages may, for example, have a tubular design, wherein the situation of the air outlet openings along the premixing passages or the corresponding delay times relative thereto may be adaptable to the frequency of the combustion chamber pressure fluctuations to be suppressed.
  • the tubular Vormischpassage consist of an elastic material whose length - and thus also the corresponding to the outlet openings delay times - is adaptable to a frequency to be suppressed.
  • Another object of the invention is to provide a gas turbine with at least one combustion chamber mentioned above, which allows a particularly effective damping of combustion chamber pressure fluctuations.
  • the gas turbine on at least one combustion chamber, which is designed according to one of claims 1 to 6.
  • a further object of the invention is to specify a burner arrangement encompassed by the initially mentioned combustion chamber, which enables a particularly effective damping of combustion chamber pressure fluctuations.
  • the burner assembly is part of the combustion chamber according to one of claims 1 to 6.
  • FIG. 1 shows a schematic sectional view of a gas turbine 1 according to the prior art.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
  • a turbine runner which is also referred to as a turbine runner.
  • an intake housing 6 a compressor 8
  • a combustion system 9 with a number of combustion chambers 10, each comprising a burner assembly 11 and a combustion chamber housing 12, a turbine 14 and an exhaust housing 15th
  • the combustion system 9 communicates with an annular hot gas duct, for example.
  • a plurality of successively connected turbine stages form the turbine 14.
  • Each turbine stage is formed of blade rings. Viewed in the flow direction of a working medium follows in the hot runner formed by a number 17 vanes row formed from blades 18 row.
  • the guide vanes 17 are fastened to an inner housing of a stator 19, whereas the moving blades 18 of a row are attached to the rotor 3, for example by means of a turbine disk.
  • Coupled to the rotor 3 is, for example, a generator (not shown).
  • the FIG. 2 shows a section of a combustion chamber 20 of a gas turbine according to an embodiment of the invention.
  • the combustion chamber 20 has a combustion chamber housing 21, which is rotationally symmetrical about an axis 22.
  • the combustion chamber housing 21 there is a first combustion zone 23 and a second combustion zone 24, the second combustion zone 24 downstream of the first combustion zone 23 with respect to a main flow direction 26.
  • the combustor 20 includes a first burner assembly (not shown) and a second burner assembly 28 for combusting a fuel / air mixture in the second combustion zone 24.
  • the second burner assembly 28 includes a premix passage 29 opening into the second combustion zone 24 for providing fuel / air A mixture, wherein in the Vormischpassage 29 an included from the second burner assembly 28 air supply 32 and a fuel supply 33 opens, the air supply 32 is stepped, so that the default in the Vormischpassage 29 outlet openings 34 of the stepped air supply 32 different delay times are assigned.
  • the second burner arrangement 28 is thus arranged in the region of a second axial step.
  • the second burner assembly 28 includes a fuel distributor ring 36 disposed outside the combustor casing 21 and a plurality of premix passages 29, the premix passages 29 having one end 37 opening into the combustor casing 21 into the second combustion zone 24 and one each from the fuel distributor ring 36 branching fuel supply 33 correspond, wherein along at least one of the Vormischpassagen 29 outlet openings 34 of a stepped air supply 32 are arranged distributed.
  • each of the Vormischpassagen 29 of the second burner assembly 28 have a stepped air supply 32.
  • the fuel injected into the premix passage 29 through the fuel supply 33 mixes with the air entering the premix passage 29 through the discharge ports 34, so that a fuel / air mixture flows in the flow direction 39 along the premix passage.
  • An air volume exiting an outlet opening 34 will mix with the fuel and will require a period of time from the position of the outlet opening 34 to enter the combustion zone 24. This period of time is referred to as the delay time and is determined by the time required for a fluid element entering the premix passage to reach the combustion zone.
  • the outlet openings 34 arranged along the premix passage 29 correspond with different delay times due to their different arrangement in the premix passage 29. Each of the outlet openings 34 in the premix passage 29 can thus be assigned different delay times.
  • FIG. 3 shows a detail view of in FIG. 2 illustrated inventive combustion chamber according to an embodiment in the region of the second burner assembly of a second axial stage. Shown is a portion of the combustor housing 21 which encloses a first combustion zone 23 (shown in part) and a second combustion zone 24 (shown in part) downstream thereof, wherein a premix passage 29 comprised by the second burner assembly provides a fuel / air mixture enters the second combustion zone 24.
  • the staged air supply 32 comprises outlet openings 34a, 34b, 34c which open into the premix passage 29 for the supply of air 40, the outlet openings 34a, 34b, 34c being different Delay times ⁇ 1 , ⁇ 2 , ⁇ 3 , are assignable. For example, an air volume exiting from the outlet opening 34a will mix with the fuel 35 flowing past the fuel supply 33 and will require a period of time ⁇ 1 from the position of the outlet opening 34a to enter the second combustion zone 24.
  • the position of the outlet openings 34a, 34b and 34c may advantageously be selected such that ⁇ 1 - ⁇ 3 > 1 / f.
  • the density fluctuations of the air caused by the combustion chamber pressure fluctuation of the frequency f in the outlet openings can be superimposed upon ignition of the fuel / air mixture in the second combustion zone 24 due to the different delay times ⁇ 1 , ⁇ 2 , ⁇ 3 in such a way that these density fluctuations occur essentially cancel each other out.
  • the arrangement of the outlet openings 34a, 34b, 34c along the premix passage 29 can be selected accordingly.
  • the combustion chamber pressure fluctuation of the frequency f may be a combustion chamber pressure fluctuation which can preferably be excited on account of the design of the combustion chamber. This may also be referred to as preferential combustion chamber pressure fluctuation.
  • a development of the illustrated embodiment may also provide that the fuel supply 33 is also formed stepped (not shown here).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP11187285.9A 2011-10-31 2011-10-31 Chambre de combustion pour une turbine à gaz et agencement de brûleur Withdrawn EP2587158A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP11187285.9A EP2587158A1 (fr) 2011-10-31 2011-10-31 Chambre de combustion pour une turbine à gaz et agencement de brûleur
CN201280065621.7A CN104024737B (zh) 2011-10-31 2012-10-19 用于燃气轮机的燃烧室和燃烧器装置
PCT/EP2012/070783 WO2013064383A1 (fr) 2011-10-31 2012-10-19 Chambre de combustion pour turbine à gaz et système de brûleurs
US14/355,467 US20140260265A1 (en) 2011-10-31 2012-10-19 Combustion chamber for a gas turbine and burner arrangement
EP12780155.3A EP2773907A1 (fr) 2011-10-31 2012-10-19 Chambre de combustion pour turbine à gaz et système de brûleurs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11187285.9A EP2587158A1 (fr) 2011-10-31 2011-10-31 Chambre de combustion pour une turbine à gaz et agencement de brûleur

Publications (1)

Publication Number Publication Date
EP2587158A1 true EP2587158A1 (fr) 2013-05-01

Family

ID=47115871

Family Applications (2)

Application Number Title Priority Date Filing Date
EP11187285.9A Withdrawn EP2587158A1 (fr) 2011-10-31 2011-10-31 Chambre de combustion pour une turbine à gaz et agencement de brûleur
EP12780155.3A Withdrawn EP2773907A1 (fr) 2011-10-31 2012-10-19 Chambre de combustion pour turbine à gaz et système de brûleurs

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP12780155.3A Withdrawn EP2773907A1 (fr) 2011-10-31 2012-10-19 Chambre de combustion pour turbine à gaz et système de brûleurs

Country Status (4)

Country Link
US (1) US20140260265A1 (fr)
EP (2) EP2587158A1 (fr)
CN (1) CN104024737B (fr)
WO (1) WO2013064383A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
WO2017155914A1 (fr) * 2016-03-10 2017-09-14 Siemens Energy, Inc. Agencement de conduits dans un système de combustion d'une turbine à gaz

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube
CN105650678B (zh) * 2016-01-11 2018-04-10 清华大学 涡轮活塞混合动力***的燃烧室进气结构
JP2018004138A (ja) * 2016-06-30 2018-01-11 川崎重工業株式会社 ガスタービン燃焼器
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1493972A1 (fr) * 2003-07-04 2005-01-05 Siemens Aktiengesellschaft Ensemble de brûleur pour une turbine à gaz et turbine à gaz
EP2078898A1 (fr) * 2008-01-11 2009-07-15 Siemens Aktiengesellschaft Brûleur et procédé pour réduire des oscillations de flammes autoinduites
EP2236932A1 (fr) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9929601D0 (en) * 1999-12-16 2000-02-09 Rolls Royce Plc A combustion chamber
US6427446B1 (en) * 2000-09-19 2002-08-06 Power Systems Mfg., Llc Low NOx emission combustion liner with circumferentially angled film cooling holes
GB2390150A (en) * 2002-06-26 2003-12-31 Alstom Reheat combustion system for a gas turbine including an accoustic screen
US9032737B2 (en) * 2009-12-30 2015-05-19 Rolls-Royce North American Technologies, Inc. Combustor added to a gas turbine engine to increase thrust

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1493972A1 (fr) * 2003-07-04 2005-01-05 Siemens Aktiengesellschaft Ensemble de brûleur pour une turbine à gaz et turbine à gaz
EP2078898A1 (fr) * 2008-01-11 2009-07-15 Siemens Aktiengesellschaft Brûleur et procédé pour réduire des oscillations de flammes autoinduites
EP2236932A1 (fr) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
CN104748151A (zh) * 2013-12-06 2015-07-01 通用电气公司 延迟贫喷射歧管混合***
WO2017155914A1 (fr) * 2016-03-10 2017-09-14 Siemens Energy, Inc. Agencement de conduits dans un système de combustion d'une turbine à gaz

Also Published As

Publication number Publication date
US20140260265A1 (en) 2014-09-18
EP2773907A1 (fr) 2014-09-10
CN104024737A (zh) 2014-09-03
CN104024737B (zh) 2016-04-06
WO2013064383A1 (fr) 2013-05-10

Similar Documents

Publication Publication Date Title
EP2587158A1 (fr) Chambre de combustion pour une turbine à gaz et agencement de brûleur
DE102010061639B4 (de) Verfahren zum Betreiben einer sekundären Brennstoffdüse für eine Brennkammer einer Turbomaschine
DE102005023536B4 (de) Vormischbrenner mit aufprallgekühltem Mittelkörper und Verfahren zum Kühlen des Mittelkörpers
DE60114912T2 (de) Verfahren und Vorrichtung zur Verminderung der Emissionen eines Gasturbinen-Triebwerkes
EP1064498B1 (fr) Bruleur pour une turbine a gas
DE102011055475A1 (de) System und Verfahren zum Einspritzen von Kraftstoff
EP0924470B1 (fr) Chambre de combustion à prémélange pour turbine à gaz
EP3134677B1 (fr) Brûleur ayant un oscillateur fluidique, pour une turbine à gaz et turbine à gaz ayant le brûleur
CH697790B1 (de) Düse zum Leiten eines Fluids in einen Brennkammeraufbau.
DE102011000589A1 (de) Axial gestufte Vormischbrennkammer
CH710573A2 (de) Brennstoffdüse für eine Gasturbinenbrennkammer.
EP3004743B1 (fr) Brûleur pour une turbine à gaz et procédé de réduction d'oscillations thermoacoustiques dans une turbine à gaz
DE102009043830A1 (de) Flammenhaltungs-toleranter Brennstoff/Luft-Vormischer für eine Gasturbinenbrennkammer
DE102007062896A1 (de) Mittelkörper für Mischeranordnung einer Gasturbinentriebwerks-Brennkammer
DE102009025775A1 (de) Vormischeinrichtung für eine Gasturbine
EP2780635A2 (fr) Chambre de combustion pour une turbine à gaz, turbine à gaz et procédé correspondant
DE112015002441B4 (de) Gasturbinenbrennkammer und Gasturbine
CH703230B1 (de) Gasturbine mit einstufiger Brennstoffeinspritzung.
EP2703720A2 (fr) Procédé de fonctionnement d'un brûleur à prémélange maigre d'une turbine à gaz pour l'aéronautique et dispositif permettant de réaliser le procédé
EP2236932A1 (fr) Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz
DE112014000656T5 (de) Gasturbinen-Einspritzvorrichtung mit Hohlraum zum Zumessen
WO2019020350A1 (fr) Brûleur de turbine à gaz à jets de flamme prémélangés
EP1662202A1 (fr) Brûleur pour une turbine à gaz et procédé d'utilisation d'un tel brûleur
EP2993406A1 (fr) Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz
EP2808612A1 (fr) Chambre de combustion d'une turbine à gaz avec injection tangentielle comme injection pauvre tardive

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): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

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: 20131105