RU92004465A - GAS TURBINE COMBUSTION CHAMBER AND METHOD FOR ITS OPERATION - Google Patents

GAS TURBINE COMBUSTION CHAMBER AND METHOD FOR ITS OPERATION

Info

Publication number
RU92004465A
RU92004465A RU92004465/06A RU92004465A RU92004465A RU 92004465 A RU92004465 A RU 92004465A RU 92004465/06 A RU92004465/06 A RU 92004465/06A RU 92004465 A RU92004465 A RU 92004465A RU 92004465 A RU92004465 A RU 92004465A
Authority
RU
Russia
Prior art keywords
burners
combustion chamber
ring
gas turbine
front wall
Prior art date
Application number
RU92004465/06A
Other languages
Russian (ru)
Other versions
RU2062408C1 (en
Inventor
Келлер Якоб
Заттельмайер Томас
Сеньор Питер
Keller Jakob
Zattel'majer Tomas
Sen'or Piter
Original Assignee
Асеа Браун Бовери АГ
Asea Braun Boveri 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
Priority claimed from CH3308/91A external-priority patent/CH684963A5/en
Application filed by Асеа Браун Бовери АГ, Asea Braun Boveri Ag filed Critical Асеа Браун Бовери АГ
Application granted granted Critical
Publication of RU2062408C1 publication Critical patent/RU2062408C1/en
Publication of RU92004465A publication Critical patent/RU92004465A/en

Links

Claims (1)

В камере сгорания газовой турбины, которая кольцеобразно окружает ротор, в связи с чем имеет форму кольцевой камеры сгорания, ее передняя стенка оснащена совокупностью горелок, которые занимают на конце единую плоскость. Эти горелки образуют на передней стенке двойное кольцо. В каждом кольце горелки имеют одинаковое направление закрутки потока, противоположное направлению закрутки в соседнем кольце. Кроме того, в каждом кольце каждые две горелки поочередно смещены наружу или к центру для того, чтобы получить благоприятное для сгорания поле потока. Совокупность горелок на передней стенка разделяется на большее число пилотирующих горелок и меньшее число пилотируемых головок.In the combustion chamber of a gas turbine, which annularly surrounds the rotor, and therefore has the shape of an annular combustion chamber, its front wall is equipped with a set of burners that occupy a single plane at the end. These burners form a double ring on the front wall. In each ring, the burners have the same direction of swirling flow, opposite to the direction of twisting in the adjacent ring. In addition, in each ring, every two burners are alternately shifted outwards or toward the center in order to obtain a favorable flow field for combustion. The set of burners on the front wall is divided into a larger number of pilot torches and a smaller number of manned heads.
RU9292004465A 1991-11-13 1992-11-12 Ring combustion chamber of gas turbine and method of using same RU2062408C1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3308/91A CH684963A5 (en) 1991-11-13 1991-11-13 Annular combustion chamber.
CH3308/91 1991-11-13

Publications (2)

Publication Number Publication Date
RU2062408C1 RU2062408C1 (en) 1996-06-20
RU92004465A true RU92004465A (en) 1996-07-27

Family

ID=4253183

Family Applications (1)

Application Number Title Priority Date Filing Date
RU9292004465A RU2062408C1 (en) 1991-11-13 1992-11-12 Ring combustion chamber of gas turbine and method of using same

Country Status (9)

Country Link
US (1) US5400587A (en)
EP (1) EP0542044B1 (en)
JP (1) JP3308610B2 (en)
KR (1) KR930010360A (en)
CA (1) CA2082862A1 (en)
CH (1) CH684963A5 (en)
DE (1) DE59204754D1 (en)
PL (1) PL169967B1 (en)
RU (1) RU2062408C1 (en)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4318405C2 (en) * 1993-06-03 1995-11-02 Mtu Muenchen Gmbh Combustion chamber arrangement for a gas turbine
US5671597A (en) * 1994-12-22 1997-09-30 United Technologies Corporation Low nox fuel nozzle assembly
DE19549143A1 (en) * 1995-12-29 1997-07-03 Abb Research Ltd Gas turbine ring combustor
GB2319078B (en) 1996-11-08 1999-11-03 Europ Gas Turbines Ltd Combustor arrangement
EP0976982B1 (en) * 1998-07-27 2003-12-03 ALSTOM (Switzerland) Ltd Method of operating the combustion chamber of a liquid-fuel gas turbine
SE9802707L (en) * 1998-08-11 2000-02-12 Abb Ab Burner chamber device and method for reducing the influence of acoustic pressure fluctuations in a burner chamber device
WO2000049337A1 (en) * 1999-02-16 2000-08-24 Siemens Aktiengesellschaft Burner arrangement and method for operating a burner arrangement
EP1065346A1 (en) 1999-07-02 2001-01-03 Asea Brown Boveri AG Gas-turbine engine combustor
US6474071B1 (en) * 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
US6772583B2 (en) 2002-09-11 2004-08-10 Siemens Westinghouse Power Corporation Can combustor for a gas turbine engine
US6931853B2 (en) 2002-11-19 2005-08-23 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
US7080515B2 (en) * 2002-12-23 2006-07-25 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
US20060156734A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Gas turbine combustor
GB2455289B (en) * 2007-12-03 2010-04-07 Siemens Ag Improvements in or relating to burners for a gas-turbine engine
US20090301054A1 (en) * 2008-06-04 2009-12-10 Simpson Stanley F Turbine system having exhaust gas recirculation and reheat
US9297306B2 (en) * 2008-09-11 2016-03-29 General Electric Company Exhaust gas recirculation system, turbomachine system having the exhaust gas recirculation system and exhaust gas recirculation control method
RU2506499C2 (en) * 2009-11-09 2014-02-10 Дженерал Электрик Компани Fuel atomisers of gas turbine with opposite swirling directions
US9127598B2 (en) 2011-08-25 2015-09-08 General Electric Company Control method for stoichiometric exhaust gas recirculation power plant
US8453461B2 (en) 2011-08-25 2013-06-04 General Electric Company Power plant and method of operation
US8205455B2 (en) 2011-08-25 2012-06-26 General Electric Company Power plant and method of operation
US8266883B2 (en) 2011-08-25 2012-09-18 General Electric Company Power plant start-up method and method of venting the power plant
US8347600B2 (en) 2011-08-25 2013-01-08 General Electric Company Power plant and method of operation
US8713947B2 (en) 2011-08-25 2014-05-06 General Electric Company Power plant with gas separation system
US8453462B2 (en) 2011-08-25 2013-06-04 General Electric Company Method of operating a stoichiometric exhaust gas recirculation power plant
US8266913B2 (en) 2011-08-25 2012-09-18 General Electric Company Power plant and method of use
US8245492B2 (en) 2011-08-25 2012-08-21 General Electric Company Power plant and method of operation
RU2581267C2 (en) * 2013-11-12 2016-04-20 Федеральное государственное бюджетное научное учреждение "Всероссийский научно-исследовательский институт электрификации сельского хозяйства" (ФГБНУ ВИЭСХ) Device for combustion chamber with adjustable swirler for micro gas turbine engine, where turbine and compressor are turbo compressor of ice
RU2561754C1 (en) 2014-02-12 2015-09-10 Открытое акционерное общество "Газпром" Ring combustion chamber of gas-turbine engine and its operation method
RU2624682C1 (en) * 2016-07-05 2017-07-05 Новиков Илья Николаевич Annular combustion chamber of gas turbine engine and method of working process implementation

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3714778A (en) * 1970-01-02 1973-02-06 Angelica Corp Annular combustor systems
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4271675A (en) * 1977-10-21 1981-06-09 Rolls-Royce Limited Combustion apparatus for gas turbine engines
US4236378A (en) * 1978-03-01 1980-12-02 General Electric Company Sectoral combustor for burning low-BTU fuel gas
DE3261484D1 (en) * 1981-03-04 1985-01-24 Bbc Brown Boveri & Cie Annular combustion chamber with an annular burner for gas turbines
DE3837635A1 (en) * 1988-11-05 1990-05-10 Proizv Ob Nevskij Z Im V I Method for burning fuel in a combustion chamber
US4991398A (en) * 1989-01-12 1991-02-12 United Technologies Corporation Combustor fuel nozzle arrangement
CH678757A5 (en) * 1989-03-15 1991-10-31 Asea Brown Boveri
CH680084A5 (en) * 1989-06-06 1992-06-15 Asea Brown Boveri

Similar Documents

Publication Publication Date Title
RU92004465A (en) GAS TURBINE COMBUSTION CHAMBER AND METHOD FOR ITS OPERATION
RU1836606C (en) Annular combustion chamber of gas turbine engine
ATE114803T1 (en) COMBUSTION CHAMBER OF A GAS TURBINE.
PL285434A1 (en) Combustion chamber of a gas turbine
GB1010338A (en) Means for supporting the downstream end of a combustion chamber in a gas turbine engine
CA2086399A1 (en) Split stream burner assembly
GB1424197A (en) Combustion chambers for gas turbine engines
KR930010360A (en) Annular combustion chamber and how it works
US5398509A (en) Gas turbine engine combustor
GB1494591A (en) Flexible interconnection for combustors of gas turbine engines
KR840003732A (en) Combustor basket for combustion turbine
US3238718A (en) Gas turbine engine
GB1344359A (en) Combustion equipment for gas turbine engines
GB1089467A (en) Improvements in or relating to gas turbines
FR2380424A1 (en) GAS TURBINE ENGINE ANNULAR COMBUSTION CHAMBER
JPS5546309A (en) Burner for gas turbine
RU92005659A (en) THE COMBUSTION CHAMBER
GB1135670A (en) Combustion chamber for a gas turbine engine
US4389188A (en) Gas burner injector head
US3556670A (en) Rotary heat engine
US5288026A (en) Flame retaining ceramic burner nozzle
GB1495066A (en) Burner heads suitable for oil burners and to burners provided with such heads
SU1442790A1 (en) Gas burner
RU93016230A (en) THE COMBUSTION CHAMBER
SU1508049A1 (en) Gas/oil burner