EP2657608A3 - A Combustor - Google Patents

A Combustor Download PDF

Info

Publication number
EP2657608A3
EP2657608A3 EP13156623.4A EP13156623A EP2657608A3 EP 2657608 A3 EP2657608 A3 EP 2657608A3 EP 13156623 A EP13156623 A EP 13156623A EP 2657608 A3 EP2657608 A3 EP 2657608A3
Authority
EP
European Patent Office
Prior art keywords
end cap
downstream
surface
portion
combustion chamber
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.)
Granted
Application number
EP13156623.4A
Other languages
German (de)
French (fr)
Other versions
EP2657608A2 (en
EP2657608B1 (en
Inventor
Won-Wook Kim
Jeffrey Scott Lebegue
Kevin Weston Mcmahan
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 Co
Original Assignee
General Electric Co
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 to US13/457,754 priority Critical patent/US20130283802A1/en
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2657608A2 publication Critical patent/EP2657608A2/en
Publication of EP2657608A3 publication Critical patent/EP2657608A3/en
Application granted granted Critical
Publication of EP2657608B1 publication Critical patent/EP2657608B1/en
Application status is Active legal-status Critical
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/425Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Abstract

A combustor includes an end cap (52) that extends radially across at least a portion of the combustor, wherein the end cap (52) comprises an upstream surface (64) axially separated from a downstream surface (66). A shroud (68) circumferentially surrounds at least a portion of the end cap (52), wherein the shroud (68) at least partially defines a fuel plenum (70) between the upstream surface (64) and the downstream surface (66). A combustion chamber (38) downstream from the end cap (52) defines a longitudinal axis. A plurality of tubes (50) extend from the upstream surface (64) through the downstream surface (66) of the end cap (52) to provide fluid communication through the end cap (52) to the combustion chamber (38). A transition duct (40) circumferentially surrounds at least a portion of the combustion chamber (38) downstream from the end cap (52) and curves tangentially from the longitudinal axis.
EP13156623.4A 2012-04-27 2013-02-25 A Combustor Active EP2657608B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US13/457,754 US20130283802A1 (en) 2012-04-27 2012-04-27 Combustor

Publications (3)

Publication Number Publication Date
EP2657608A2 EP2657608A2 (en) 2013-10-30
EP2657608A3 true EP2657608A3 (en) 2013-12-11
EP2657608B1 EP2657608B1 (en) 2015-12-16

Family

ID=47750510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13156623.4A Active EP2657608B1 (en) 2012-04-27 2013-02-25 A Combustor

Country Status (5)

Country Link
US (1) US20130283802A1 (en)
EP (1) EP2657608B1 (en)
JP (1) JP2013231575A (en)
CN (1) CN103375811A (en)
RU (1) RU2013108310A (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6262616B2 (en) * 2014-08-05 2018-01-17 三菱日立パワーシステムズ株式会社 Gas turbine combustor
EP3026346A1 (en) * 2014-11-25 2016-06-01 Alstom Technology Ltd Combustor liner
KR20190004612A (en) * 2017-07-04 2019-01-14 두산중공업 주식회사 Fuel nozzle assembly and combustor and gas turbine having the same
CN107702144A (en) * 2017-09-05 2018-02-16 中国联合重型燃气轮机技术有限公司 Combustor and combustion gas turbine with combustor

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100115953A1 (en) * 2008-11-12 2010-05-13 Davis Jr Lewis Berkley Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method
EP2213944A2 (en) * 2009-02-02 2010-08-04 General Electric Company Apparatus for fuel injection in a turbine engine
US20100300102A1 (en) * 2009-05-28 2010-12-02 General Electric Company Method and apparatus for air and fuel injection in a turbine

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
DE2950535A1 (en) * 1979-11-23 1981-06-11 Bbc Brown Boveri & Cie Combustor of a gas turbine with premixed / vorverdampf-elements
JP2528894B2 (en) * 1987-09-04 1996-08-28 株式会社日立製作所 Antofagasta - turbine combustor
US5361586A (en) * 1993-04-15 1994-11-08 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor
JP3956882B2 (en) * 2002-08-22 2007-08-08 株式会社日立製作所 Method for retrofitting a gas turbine combustor and a gas turbine combustor
US7721547B2 (en) * 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
JP4959620B2 (en) * 2007-04-26 2012-06-27 株式会社日立製作所 The method of the fuel supply combustor and the combustor
US9140454B2 (en) * 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
US8424311B2 (en) * 2009-02-27 2013-04-23 General Electric Company Premixed direct injection disk
US8616002B2 (en) * 2009-07-23 2013-12-31 General Electric Company Gas turbine premixing systems
JP5103454B2 (en) * 2009-09-30 2012-12-19 株式会社日立製作所 Combustor
US8276385B2 (en) * 2009-10-08 2012-10-02 General Electric Company Staged multi-tube premixing injector
US20110259015A1 (en) * 2010-04-27 2011-10-27 David Richard Johns Tangential Combustor
US20120058437A1 (en) * 2010-09-08 2012-03-08 General Electric Company Apparatus and method for mixing fuel in a gas turbine nozzle
US8984887B2 (en) * 2011-09-25 2015-03-24 General Electric Company Combustor and method for supplying fuel to a combustor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100115953A1 (en) * 2008-11-12 2010-05-13 Davis Jr Lewis Berkley Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method
EP2213944A2 (en) * 2009-02-02 2010-08-04 General Electric Company Apparatus for fuel injection in a turbine engine
US20100300102A1 (en) * 2009-05-28 2010-12-02 General Electric Company Method and apparatus for air and fuel injection in a turbine

Also Published As

Publication number Publication date
US20130283802A1 (en) 2013-10-31
EP2657608A2 (en) 2013-10-30
JP2013231575A (en) 2013-11-14
EP2657608B1 (en) 2015-12-16
RU2013108310A (en) 2014-09-10
CN103375811A (en) 2013-10-30

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