EP0781967B1 - Gasturbinenringbrennkammer - Google Patents

Gasturbinenringbrennkammer Download PDF

Info

Publication number
EP0781967B1
EP0781967B1 EP96810777A EP96810777A EP0781967B1 EP 0781967 B1 EP0781967 B1 EP 0781967B1 EP 96810777 A EP96810777 A EP 96810777A EP 96810777 A EP96810777 A EP 96810777A EP 0781967 B1 EP0781967 B1 EP 0781967B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas
air
turbine
chamber according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP96810777A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0781967A3 (de
EP0781967A2 (de
Inventor
Klaus Dr. Döbbeling
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0781967A2 publication Critical patent/EP0781967A2/de
Publication of EP0781967A3 publication Critical patent/EP0781967A3/de
Application granted granted Critical
Publication of EP0781967B1 publication Critical patent/EP0781967B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to the field of combustion technology. It relates to a gas turbine ring combustion chamber, which is operated with premix burners, and a method for Operation of this device.
  • Gas turbines essentially consist of the components compressor, Combustion chamber and turbine. For environmental reasons is increased instead of diffusion combustion worked with a low-pollutant premix combustion.
  • the air coming out of the compressor is very high Speed (approx. 200 m / s) and is to the contained in it Recover kinetic energy, as lossless as possible delayed in a deflection diffuser.
  • the speed in the combustion chamber strong at least locally downstream of the burner lowered. Usually a local recirculation zone with negative Speeds generated. In the combustion chamber the speed then about 50 m / s to a sufficient Preservation time and the heat transfer between hot gas and to keep the combustion chamber wall small. At the exit of the The combustion chamber accelerates again, so that on Entry of the turbine speeds up to close to the gas the speed of sound can be reached.
  • the invention tries to avoid all these disadvantages. you is based on the task of a gas turbine ring combustion chamber, which is equipped with special premix burners develop, which is characterized by a small size and simplified compared to the known prior art is, with improved premixing of fuel and Air occurs with a lower total pressure drop.
  • this is done in a gas turbine ring combustion chamber, which is arranged downstream of a compressor and on it Front plate with at least one arranged in a ring Premix burner row is equipped, achieved by direct downstream of the compressor outlet from the guide vanes of the last compressor series for each burner one as Diffuser-trained burner air duct leads to the latter downstream end there is at least one longitudinal vortex generator is located, at least in or downstream of the longitudinal vortex generator a fuel injection is provided and downstream the fuel injection ends in the combustion chamber Mixing channel of constant channel height and with a length that is approximately corresponds to twice the hydraulic duct height, is arranged.
  • the combustion air is released immediately after it leaves the compressor into individual air flows for the burners and for the Cooling of the combustion chamber and turbine split, after that the speed of the air for the burners to about that delayed half the value of the compressor outlet speed, then at least one longitudinal vortex per combustion air duct generated in the air, during or downstream of the Longitudinal vortex generation fuel is added to the mixture now flows along in a mixing channel and with a total swirl contaminated flows into the combustion chamber and there finally burns.
  • the advantages of the invention include that the combustion chamber compared to the prior art has smaller dimensions and the area to be cooled in the Combustion chamber is reduced. The pressure loss between the compressor outlet and turbine entry is smaller. Furthermore there is a very good and robust uniform distribution of the air on the burners and the premixing of fuel and combustion air will be improved.
  • the ratio of the number the blades of the last row of compressors to the number of premix burners is an integer, especially 1 or 2, because then a combustion air duct directly to one or two blade ducts the last row of compressors can be coupled.
  • the mixing channel is approximately rounded Cross-section, because then a good mixing of air and fuel is achieved. But also mixed channels with a rectangular cross section are conceivable. Likewise can if there is only one burner row, the mixing channel be designed as a segmented annular gap.
  • combustion air channels are spiral are arranged around the axis of the gas turbine. In this way axial length can be saved.
  • the axes of the mixing channels are advantageous (i.e. the direction of flow of the entering the combustion chamber Mixture), arranged so that it coincides with the axis of the Gas turbine an angle, preferably an angle of 45 °, form. This will allow the mixture and flame stabilization further improved.
  • FIG. 1 shows a partial longitudinal section of a gas turbine system with an annular combustion chamber according to the prior art.
  • an annular combustion chamber 4 Between a compressor 1 and a turbine 2, of which only one guide vane 3 of the first row of guide vanes is shown is an annular combustion chamber 4, which with premix burners 5 of the double cone design is equipped, arranged.
  • the supply of fuel 6 to each premix burner 5 is realized over fuel lances 7.
  • the annular combustion chamber 4 is cooled convectively or by means of impingement cooling.
  • the compressor 1 essentially consists of the blade carrier 8, in which the guide vanes 9 are hooked in and out of the rotor 10, which receives the blades 11. In Fig. 1 are each only the last compressor stages are shown.
  • a deflection diffuser 12 At the exit of the Compressor 1, a deflection diffuser 12 is arranged. It ends in a arranged between the compressor 1 and the annular combustion chamber 4 Plenary 13.
  • the air 14 emerging from the compressor 1 has a very high high speed. It is delayed in the deflection diffuser 12, to recover the kinetic energy it contains so that in the adjoining the deflection diffuser 12 Plenary 13 only very low air speeds to rule. This can result in a uniform distribution of the air 14 the burner 5 can be reached and there can be cooling air without any problems for the combustion chamber 4 and the turbine 2 are removed. There but on the other hand for the reliable design of the premixing process of air 14 and fuel 6 at the mixing point the fuel 6 the speed in order to avoid must be high from flashback, the air 14 in the premixing zone be accelerated again strongly before again downstream of the burner 5 in the combustion chamber 4 for reasons of flame stability the speed is reduced.
  • Air 14 is no longer delayed to plenary conditions, but instead the delay in the air 14 is only limited to that Speed level of the premix section. This allows the multiple redirection of the total air mass flow is eliminated and the size of the combustion chamber is significantly reduced become.
  • each burner 5 of the annular combustion chamber 4 each designed as a diffuser Burner air duct 15 leads.
  • At least one fuel injection 17 is provided and downstream of the fuel injection 17 is in the combustion chamber 4 ending mixing channel 19 of constant height H and with a length L, which is about twice the value of the hydraulic channel diameter D corresponds to arranged.
  • the deflection diffuser 12 and 12 is therefore omitted plenary session 13.
  • the air from the compressor 1 is immediately after the outlet from the compressor 1 into a large number of individual channels divided, namely into the combustion air channels 15 and in annular Channels 20 arranged on the hub side or housing side for the cooling air 21 of the combustion chamber 4 and the turbine 2, the is provided here at a high pressure level. Furthermore can air 22 from the channels 20 for flushing out the Mixing channel 19 forming boundary layer can be removed. This is only an example for the innermost mixing channel 19 shown.
  • the combustion air channels 15 are designed as diffusers and delay the air speed to about half the value the compressor outlet speed, with a maximum of 75% of the dynamic energy can be converted into pressure gain.
  • the longitudinal vortex generator 16 After the combustion air 14 to an appropriate speed level was delayed at the longitudinal vortex generator 16 generates one or more longitudinal vortices per combustion air duct 15.
  • the longitudinal vortex generator 16 is an integrated Fuel injection 17 fuel 6, which for example is supplied by fuel lances 7, mixed with the air 14.
  • the fuel injection 17 also downstream of the longitudinal vortex generator 16 may be arranged.
  • the longitudinal vortices generated guarantee a good mixture of fuel 6 and combustion air 14 in the subsequent mixing channels 19. These have a constant height H and are approximately double as long as two hydraulic channel diameters D.
  • the mixing channels 19 have a circular shape Cross section, are therefore a mixing tube.
  • the mixing tube axes 24 are arranged parallel to the axis 25 of the gas turbine.
  • the mixing channels 19 not shown here in the drawing can the mixing channels 19 a right or have polygonal cross-section or they can also be a segmented annular gap.
  • FIGS. 1 and 2 the reduction in the area of the combustion chamber wall to be cooled can be clearly seen according to the invention.
  • a gas turbine from the 170 MWel class, eg GT13E2 should serve as an example. While according to the prior art (FIG. 1) the outer diameter in the area of the combustion chamber is approximately 4.5 m, this value is only 3.5 m when using the invention, so that the size is reduced by approx. 20% is reached. Due to the greatly reduced area to be cooled in the new combustion chamber and the extremely low NOx emissions that can be achieved with good premix burner technology at relatively high flame temperatures (theoretically approx. 5 ppm NOx at 15% O 2 and 1850 K flame temperature), the combustion chamber can be cooled via film or effusion cooling.
  • FIG. 3 is a partial cross section of a two-row annular combustion chamber corresponding to a section in the plane III-III of the in Fig. 2 shown four-row combustion chamber.
  • the annular combustion chamber 4 according to FIG. 3 is thus with two rows Premix burners 5 equipped.
  • the arrows in Fig. 3 are intended an opposite angle of attack of the burner 5 in the side by side Clarify rows. By this opposite Angle of attack is achieved in the combustion chamber 4 no total swirl is generated.
  • the cross section of the mixing channels 19 is not round in this embodiment, but elliptical.
  • the mixing tube axes 24 are opposite the shaft in the circumferential direction, i.e. the mixing tube axis 24 forms an angle of ⁇ with the machine axis 25 approx. 45 °. This will allow the mixture and flame stabilization improved in the combustion chamber 4.
  • combustion air channels 15 spiral about the axis 25 of the Gas turbine arranged to the axial length of the machine to keep it as small as possible.
  • the invention is particularly suitable for the use of MBtu as fuel, i.e. fuel with a medium calorific value, for example in the gasification of heavy oil, coal and Tar arises.
  • the fuel admixture can be used in this case very easily into a higher speed range (> 100 m / s) to be relocated to these fuels, too are characterized by a high flame speed, to avoid backfire to the fuel injector.
  • the high-frequency generated by the last row of compressor runs (> 1000 Hz) pressure pulsations (wake of the blades) particularly support the fuel-air mixing process, because between the end of the compressor 1 and the fuel injection 17 only a short delay section, i.e. a short burner air duct 15 designed as a diffuser, is required

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP96810777A 1995-12-29 1996-11-12 Gasturbinenringbrennkammer Expired - Lifetime EP0781967B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19549143 1995-12-29
DE19549143A DE19549143A1 (de) 1995-12-29 1995-12-29 Gasturbinenringbrennkammer

Publications (3)

Publication Number Publication Date
EP0781967A2 EP0781967A2 (de) 1997-07-02
EP0781967A3 EP0781967A3 (de) 1999-04-07
EP0781967B1 true EP0781967B1 (de) 2003-04-02

Family

ID=7781645

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810777A Expired - Lifetime EP0781967B1 (de) 1995-12-29 1996-11-12 Gasturbinenringbrennkammer

Country Status (5)

Country Link
US (1) US5839283A (zh)
EP (1) EP0781967B1 (zh)
JP (1) JPH09196379A (zh)
CN (1) CN1088151C (zh)
DE (2) DE19549143A1 (zh)

Families Citing this family (135)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6119459A (en) * 1998-08-18 2000-09-19 Alliedsignal Inc. Elliptical axial combustor swirler
DE19914666B4 (de) * 1999-03-31 2009-08-20 Alstom Brenner für einen Wärmeerzeuger
US6564555B2 (en) 2001-05-24 2003-05-20 Allison Advanced Development Company Apparatus for forming a combustion mixture in a gas turbine engine
US6405703B1 (en) 2001-06-29 2002-06-18 Brian Sowards Internal combustion engine
US7603841B2 (en) * 2001-07-23 2009-10-20 Ramgen Power Systems, Llc Vortex combustor for low NOx emissions when burning lean premixed high hydrogen content fuel
US7003961B2 (en) * 2001-07-23 2006-02-28 Ramgen Power Systems, Inc. Trapped vortex combustor
US6694743B2 (en) 2001-07-23 2004-02-24 Ramgen Power Systems, Inc. Rotary ramjet engine with flameholder extending to running clearance at engine casing interior wall
JP2003065537A (ja) * 2001-08-24 2003-03-05 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
JP2003074854A (ja) * 2001-08-28 2003-03-12 Honda Motor Co Ltd ガスタービン・エンジンの燃焼器
JP2003074853A (ja) * 2001-08-28 2003-03-12 Honda Motor Co Ltd ガスタービン・エンジンの燃焼器
EP1507120A1 (de) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Gasturbine
IL165233A (en) * 2004-11-16 2013-06-27 Israel Hirshberg Energy conversion facility
US20060156734A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Gas turbine combustor
DE102006004840A1 (de) * 2006-02-02 2007-08-23 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Kraftstoffeinspritzung über den gesamten Brennkammerring
WO2007102807A1 (en) * 2006-03-06 2007-09-13 United Technologies Corporation Angled flow annular combustor for turbine engine
FR2917487B1 (fr) * 2007-06-14 2009-10-02 Snecma Sa Chambre de combustion de turbomachine a circulation helicoidale de l'air
CN101981162B (zh) 2008-03-28 2014-07-02 埃克森美孚上游研究公司 低排放发电和烃采收系统及方法
MY156350A (en) 2008-03-28 2016-02-15 Exxonmobil Upstream Res Co Low emission power generation and hydrocarbon recovery systems and methods
US20090241547A1 (en) * 2008-03-31 2009-10-01 Andrew Luts Gas turbine fuel injector for lower heating capacity fuels
CA2737133C (en) 2008-10-14 2017-01-31 Exxonmobil Upstream Research Company Methods and systems for controlling the products of combustion
US8221073B2 (en) * 2008-12-22 2012-07-17 Pratt & Whitney Canada Corp. Exhaust gas discharge system and plenum
US8133017B2 (en) * 2009-03-19 2012-03-13 General Electric Company Compressor diffuser
US8474266B2 (en) * 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle
DE102009046066A1 (de) 2009-10-28 2011-05-12 Man Diesel & Turbo Se Brenner für eine Turbine und damit ausgerüstete Gasturbine
SG10201407421UA (en) 2009-11-12 2014-12-30 Exxonmobil Upstream Res Co Low emission power generation and hydrocarbon recovery systems and methods
US8381532B2 (en) * 2010-01-27 2013-02-26 General Electric Company Bled diffuser fed secondary combustion system for gas turbines
DE102010023816A1 (de) * 2010-06-15 2011-12-15 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammeranordnung
EP2397764A1 (de) * 2010-06-18 2011-12-21 Siemens Aktiengesellschaft Turbinenbrenner
CN105863844B (zh) 2010-07-02 2017-11-14 埃克森美孚上游研究公司 低排放动力产生系统和方法
MY160832A (en) 2010-07-02 2017-03-31 Exxonmobil Upstream Res Co Stoichiometric combustion with exhaust gas recirculation and direct contact cooler
SG186084A1 (en) 2010-07-02 2013-01-30 Exxonmobil Upstream Res Co Low emission triple-cycle power generation systems and methods
CA2801494C (en) 2010-07-02 2018-04-17 Exxonmobil Upstream Research Company Stoichiometric combustion of enriched air with exhaust gas recirculation
TWI563166B (en) 2011-03-22 2016-12-21 Exxonmobil Upstream Res Co Integrated generation systems and methods for generating power
TWI564474B (zh) 2011-03-22 2017-01-01 艾克頌美孚上游研究公司 於渦輪系統中控制化學計量燃燒的整合系統和使用彼之產生動力的方法
TWI593872B (zh) 2011-03-22 2017-08-01 艾克頌美孚上游研究公司 整合系統及產生動力之方法
TWI563165B (en) 2011-03-22 2016-12-21 Exxonmobil Upstream Res Co Power generation system and method for generating power
US8978388B2 (en) 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
US8448450B2 (en) 2011-07-05 2013-05-28 General Electric Company Support assembly for transition duct in turbine system
US8650852B2 (en) 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system
DE102011108887A1 (de) 2011-07-28 2013-01-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenzentripetalringbrennkammer sowie Verfahren zur Strömungsführung
US9328623B2 (en) * 2011-10-05 2016-05-03 General Electric Company Turbine system
EP2587021A1 (en) 2011-10-24 2013-05-01 Siemens Aktiengesellschaft Gas turbine and method for guiding compressed fluid in a gas turbine
FR2982010B1 (fr) * 2011-10-26 2013-11-08 Snecma Chambre de combustion annulaire dans une turbomachine
US8974179B2 (en) 2011-11-09 2015-03-10 General Electric Company Convolution seal for transition duct in turbine system
US8459041B2 (en) 2011-11-09 2013-06-11 General Electric Company Leaf seal for transition duct in turbine system
US8701415B2 (en) 2011-11-09 2014-04-22 General Electric Company Flexible metallic seal for transition duct in turbine system
WO2013095829A2 (en) 2011-12-20 2013-06-27 Exxonmobil Upstream Research Company Enhanced coal-bed methane production
US9353682B2 (en) 2012-04-12 2016-05-31 General Electric Company Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation
US9784185B2 (en) 2012-04-26 2017-10-10 General Electric Company System and method for cooling a gas turbine with an exhaust gas provided by the gas turbine
US10273880B2 (en) 2012-04-26 2019-04-30 General Electric Company System and method of recirculating exhaust gas for use in a plurality of flow paths in a gas turbine engine
US9038394B2 (en) 2012-04-30 2015-05-26 General Electric Company Convolution seal for transition duct in turbine system
US9133722B2 (en) 2012-04-30 2015-09-15 General Electric Company Transition duct with late injection in turbine system
CA2830031C (en) 2012-10-23 2016-03-15 Alstom Technology Ltd. Burner for a can combustor
US10107495B2 (en) 2012-11-02 2018-10-23 General Electric Company Gas turbine combustor control system for stoichiometric combustion in the presence of a diluent
US9869279B2 (en) 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor
US10215412B2 (en) 2012-11-02 2019-02-26 General Electric Company System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system
US9574496B2 (en) 2012-12-28 2017-02-21 General Electric Company System and method for a turbine combustor
US9599070B2 (en) 2012-11-02 2017-03-21 General Electric Company System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system
US9611756B2 (en) 2012-11-02 2017-04-04 General Electric Company System and method for protecting components in a gas turbine engine with exhaust gas recirculation
US9631815B2 (en) 2012-12-28 2017-04-25 General Electric Company System and method for a turbine combustor
US9803865B2 (en) 2012-12-28 2017-10-31 General Electric Company System and method for a turbine combustor
US9708977B2 (en) 2012-12-28 2017-07-18 General Electric Company System and method for reheat in gas turbine with exhaust gas recirculation
US10161312B2 (en) 2012-11-02 2018-12-25 General Electric Company System and method for diffusion combustion with fuel-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system
US10208677B2 (en) 2012-12-31 2019-02-19 General Electric Company Gas turbine load control system
US8707673B1 (en) 2013-01-04 2014-04-29 General Electric Company Articulated transition duct in turbomachine
US9581081B2 (en) 2013-01-13 2017-02-28 General Electric Company System and method for protecting components in a gas turbine engine with exhaust gas recirculation
US9512759B2 (en) 2013-02-06 2016-12-06 General Electric Company System and method for catalyst heat utilization for gas turbine with exhaust gas recirculation
TW201502356A (zh) 2013-02-21 2015-01-16 Exxonmobil Upstream Res Co 氣渦輪機排氣中氧之減少
US9938861B2 (en) 2013-02-21 2018-04-10 Exxonmobil Upstream Research Company Fuel combusting method
US10221762B2 (en) 2013-02-28 2019-03-05 General Electric Company System and method for a turbine combustor
US9618261B2 (en) 2013-03-08 2017-04-11 Exxonmobil Upstream Research Company Power generation and LNG production
US9784182B2 (en) 2013-03-08 2017-10-10 Exxonmobil Upstream Research Company Power generation and methane recovery from methane hydrates
US20140250945A1 (en) 2013-03-08 2014-09-11 Richard A. Huntington Carbon Dioxide Recovery
TW201500635A (zh) 2013-03-08 2015-01-01 Exxonmobil Upstream Res Co 處理廢氣以供用於提高油回收
US9080447B2 (en) 2013-03-21 2015-07-14 General Electric Company Transition duct with divided upstream and downstream portions
TWI654368B (zh) 2013-06-28 2019-03-21 美商艾克頌美孚上游研究公司 用於控制在廢氣再循環氣渦輪機系統中的廢氣流之系統、方法與媒體
US9617914B2 (en) 2013-06-28 2017-04-11 General Electric Company Systems and methods for monitoring gas turbine systems having exhaust gas recirculation
US9631542B2 (en) 2013-06-28 2017-04-25 General Electric Company System and method for exhausting combustion gases from gas turbine engines
US9835089B2 (en) 2013-06-28 2017-12-05 General Electric Company System and method for a fuel nozzle
US9587510B2 (en) 2013-07-30 2017-03-07 General Electric Company System and method for a gas turbine engine sensor
US9903588B2 (en) 2013-07-30 2018-02-27 General Electric Company System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation
US9951658B2 (en) 2013-07-31 2018-04-24 General Electric Company System and method for an oxidant heating system
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters
US9458732B2 (en) 2013-10-25 2016-10-04 General Electric Company Transition duct assembly with modified trailing edge in turbine system
US9752458B2 (en) 2013-12-04 2017-09-05 General Electric Company System and method for a gas turbine engine
US10030588B2 (en) 2013-12-04 2018-07-24 General Electric Company Gas turbine combustor diagnostic system and method
US10227920B2 (en) 2014-01-15 2019-03-12 General Electric Company Gas turbine oxidant separation system
US9915200B2 (en) 2014-01-21 2018-03-13 General Electric Company System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation
US9863267B2 (en) 2014-01-21 2018-01-09 General Electric Company System and method of control for a gas turbine engine
US9631814B1 (en) * 2014-01-23 2017-04-25 Honeywell International Inc. Engine assemblies and methods with diffuser vane count and fuel injection assembly count relationships
US10079564B2 (en) 2014-01-27 2018-09-18 General Electric Company System and method for a stoichiometric exhaust gas recirculation gas turbine system
US10047633B2 (en) 2014-05-16 2018-08-14 General Electric Company Bearing housing
US9885290B2 (en) 2014-06-30 2018-02-06 General Electric Company Erosion suppression system and method in an exhaust gas recirculation gas turbine system
US10655542B2 (en) 2014-06-30 2020-05-19 General Electric Company Method and system for startup of gas turbine system drive trains with exhaust gas recirculation
US10060359B2 (en) 2014-06-30 2018-08-28 General Electric Company Method and system for combustion control for gas turbine system with exhaust gas recirculation
US9851107B2 (en) * 2014-07-18 2017-12-26 Ansaldo Energia Ip Uk Limited Axially staged gas turbine combustor with interstage premixer
US9869247B2 (en) 2014-12-31 2018-01-16 General Electric Company Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation
US9819292B2 (en) 2014-12-31 2017-11-14 General Electric Company Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine
US10788212B2 (en) 2015-01-12 2020-09-29 General Electric Company System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation
US10316746B2 (en) 2015-02-04 2019-06-11 General Electric Company Turbine system with exhaust gas recirculation, separation and extraction
US10253690B2 (en) 2015-02-04 2019-04-09 General Electric Company Turbine system with exhaust gas recirculation, separation and extraction
US10094566B2 (en) 2015-02-04 2018-10-09 General Electric Company Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation
US10267270B2 (en) 2015-02-06 2019-04-23 General Electric Company Systems and methods for carbon black production with a gas turbine engine having exhaust gas recirculation
US10145269B2 (en) 2015-03-04 2018-12-04 General Electric Company System and method for cooling discharge flow
US10480792B2 (en) 2015-03-06 2019-11-19 General Electric Company Fuel staging in a gas turbine engine
US10465907B2 (en) * 2015-09-09 2019-11-05 General Electric Company System and method having annular flow path architecture
RU2015156419A (ru) 2015-12-28 2017-07-04 Дженерал Электрик Компани Узел топливной форсунки, выполненный со стабилизатором пламени предварительно перемешанной смеси
US10260424B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10260752B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10227883B2 (en) 2016-03-24 2019-03-12 General Electric Company Transition duct assembly
US10145251B2 (en) 2016-03-24 2018-12-04 General Electric Company Transition duct assembly
US10260360B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly
US10584876B2 (en) * 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10584880B2 (en) * 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10605459B2 (en) * 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10352569B2 (en) 2016-11-04 2019-07-16 General Electric Company Multi-point centerbody injector mini mixing fuel nozzle assembly
US10393382B2 (en) 2016-11-04 2019-08-27 General Electric Company Multi-point injection mini mixing fuel nozzle assembly
US10724740B2 (en) 2016-11-04 2020-07-28 General Electric Company Fuel nozzle assembly with impingement purge
US10465909B2 (en) 2016-11-04 2019-11-05 General Electric Company Mini mixing fuel nozzle assembly with mixing sleeve
US10295190B2 (en) 2016-11-04 2019-05-21 General Electric Company Centerbody injector mini mixer fuel nozzle assembly
US10634353B2 (en) 2017-01-12 2020-04-28 General Electric Company Fuel nozzle assembly with micro channel cooling
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
CN111396926B (zh) * 2020-04-02 2021-12-07 西北工业大学 一种放气式扩压器与火焰筒一体式的燃烧室
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
KR102663869B1 (ko) 2022-01-18 2024-05-03 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
CN114576655A (zh) * 2022-03-09 2022-06-03 西北工业大学 一种扰流柱带风扇的燃烧室火焰筒壁层板冷却结构
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages
US20240068402A1 (en) * 2022-08-25 2024-02-29 Collins Engine Nozzles, Inc. Fuel injectors assemblies with tangential flow component

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2627721A (en) * 1947-01-30 1953-02-10 Packard Motor Car Co Combustion means for jet propulsion units
GB1048968A (en) * 1964-05-08 1966-11-23 Rolls Royce Combustion chamber for a gas turbine engine
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
GB1581050A (en) * 1976-12-23 1980-12-10 Rolls Royce Combustion equipment for gas turbine engines
EP0059490B1 (de) * 1981-03-04 1984-12-12 BBC Aktiengesellschaft Brown, Boveri & Cie. Ringbrennkammer mit Ringbrenner für Gasturbinen
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
US4991398A (en) * 1989-01-12 1991-02-12 United Technologies Corporation Combustor fuel nozzle arrangement
US5207064A (en) * 1990-11-21 1993-05-04 General Electric Company Staged, mixed combustor assembly having low emissions
CH684963A5 (de) * 1991-11-13 1995-02-15 Asea Brown Boveri Ringbrennkammer.
FR2711771B1 (fr) * 1993-10-27 1995-12-01 Snecma Diffuseur de chambre à alimentation circonférentielle variable.
DE4411623A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Vormischbrenner
DE4419338A1 (de) * 1994-06-03 1995-12-07 Abb Research Ltd Gasturbine und Verfahren zu ihrem Betrieb
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine

Also Published As

Publication number Publication date
DE59610298D1 (de) 2003-05-08
EP0781967A3 (de) 1999-04-07
US5839283A (en) 1998-11-24
CN1088151C (zh) 2002-07-24
CN1158383A (zh) 1997-09-03
EP0781967A2 (de) 1997-07-02
JPH09196379A (ja) 1997-07-29
DE19549143A1 (de) 1997-07-03

Similar Documents

Publication Publication Date Title
EP0781967B1 (de) Gasturbinenringbrennkammer
DE4426351B4 (de) Brennkammer für eine Gasturbine
EP0597138B1 (de) Gasturbinen-Brennkammer
DE69828916T2 (de) Emissionsarmes Verbrennungssystem für Gasturbinentriebwerke
DE102007004864C5 (de) Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
DE4406399B4 (de) Wärmeerzeuger
DE19615910B4 (de) Brenneranordnung
EP1141628B1 (de) Brenner zum betrieb eines wärmeerzeugers
EP1800062B1 (de) Brenner zur verbrennung eines niederkalorischen brenngases und verfahren zum betrieb eines brenners
EP1654496B1 (de) Brenner und verfahren zum betrieb einer gasturbine
EP0687860A2 (de) Brennkammer mit Selbstzündung
EP0620362A1 (de) Gasturbogruppe
CH708992A2 (de) Brennstoffinjektor mit Vormisch-Pilotdüse.
DE4415315A1 (de) Kraftwerksanlage
EP0733861A2 (de) Brennkammer mit Zweistufenverbrennung
EP0718561B1 (de) Brennkammer
DE102013108725A1 (de) System und Verfahren zur Reduktion von Verbrennungsdynamiken
EP2006606A1 (de) Drallfreie Stabilisierung der Flamme eines Vormischbrenners
WO2014191495A1 (de) Gasturbinen-ringbrennkammer mit tangentialeindüsung als späte mager-einspritzung
EP1207350B1 (de) Brennkammer und Verfahren zum Betrieb dieser Brennkammer
EP0924470A2 (de) Vormischbrennkammer für eine Gasturbine
CH701773B1 (de) Brenner mit einem Einlassleitschaufelsystem.
DE2222366A1 (de) Vergasersystem mit ringspalt fuer brennstoff/luft fuer den brenner von gasturbinenmaschinen
DE3821078A1 (de) Ringvergasungsbrenner fuer gasturbine
DE112016003028T5 (de) Brennstoffdüsenanordnung

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: A2

Designated state(s): DE FR GB IT

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): DE FR GB IT

17P Request for examination filed

Effective date: 19990614

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM (SWITZERLAND) LTD

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 59610298

Country of ref document: DE

Date of ref document: 20030508

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20031029

Year of fee payment: 8

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

Ref country code: DE

Payment date: 20031103

Year of fee payment: 8

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

Ref country code: FR

Payment date: 20031107

Year of fee payment: 8

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20040105

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20041112

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050601

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20041112

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050729

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20051112