BR102013027397A8 - Transição no combustor - Google Patents

Transição no combustor

Info

Publication number
BR102013027397A8
BR102013027397A8 BR102013027397A BR102013027397A BR102013027397A8 BR 102013027397 A8 BR102013027397 A8 BR 102013027397A8 BR 102013027397 A BR102013027397 A BR 102013027397A BR 102013027397 A BR102013027397 A BR 102013027397A BR 102013027397 A8 BR102013027397 A8 BR 102013027397A8
Authority
BR
Brazil
Prior art keywords
combustor
transition
turbine
gas turbine
downstream
Prior art date
Application number
BR102013027397A
Other languages
English (en)
Other versions
BR102013027397A2 (pt
Inventor
Düsing Michael
Ruben Bothien Mirko
Original Assignee
Alstom Technology Ltd
General Electric Technology Gmbh
Ansaldo Energia Switzerland 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 Technology Ltd, General Electric Technology Gmbh, Ansaldo Energia Switzerland AG filed Critical Alstom Technology Ltd
Publication of BR102013027397A2 publication Critical patent/BR102013027397A2/pt
Publication of BR102013027397A8 publication Critical patent/BR102013027397A8/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • 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
    • F23R3/002—Wall structures
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Testing Of Engines (AREA)

Abstract

TRANSIÇÃO NO COMBUSTOR. A presente invenção refere-se a uma transição no combustor (24) adaptada para guiar gases de combustão em um curso de fluxo de gases quentes (15) estendendo-se entre um combustor com câmaras (2) e um primeiro estágio de turbina (3) em uma turbina a gás (9). A transição no combustor (24) compreende um duto tendo uma extremidade a montante adaptada para conexão com o combustor com câmaras (2) e uma extremidade a jusante adaptada para conexão a um primeiro estágio de uma turbina (3), em que a extremidade a jusante compreende uma parede externa (11), uma parede interna (12), uma primeira e uma segunda paredes laterais (21a, 21b). A transição no combustor é caracterizada pelo fato de pelo menos uma parede lateral (21a, 21 b) ter uma extensão de parede lateral (20, 20a, 20b), que está se estendendo em uma direção a jusante além da saída (22). Além da transição no combustor (24), uma turbina a gás compreendendo essa transição no combustor (24), um método para retroadaptação de uma turbina a gás (9) com essa transição no combustor (24), bem como um método para inspeção por boroscópio de uma GT com essa transição no combustor são descritos.
BR102013027397A 2012-10-24 2013-10-24 Transição no combustor BR102013027397A8 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12189723.5A EP2725197A1 (en) 2012-10-24 2012-10-24 Combustor transition

Publications (2)

Publication Number Publication Date
BR102013027397A2 BR102013027397A2 (pt) 2014-12-30
BR102013027397A8 true BR102013027397A8 (pt) 2017-08-08

Family

ID=47073338

Family Applications (1)

Application Number Title Priority Date Filing Date
BR102013027397A BR102013027397A8 (pt) 2012-10-24 2013-10-24 Transição no combustor

Country Status (9)

Country Link
US (1) US9482106B2 (pt)
EP (2) EP2725197A1 (pt)
JP (1) JP5726268B2 (pt)
KR (1) KR101576455B1 (pt)
CN (1) CN103776057B (pt)
BR (1) BR102013027397A8 (pt)
CA (1) CA2830683C (pt)
RU (1) RU2566867C2 (pt)
SA (1) SA113340952B1 (pt)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10132175B2 (en) * 2014-10-07 2018-11-20 Siemens Energy, Inc. Arrangement for a gas turbine combustion engine
EP3064837B1 (en) 2015-03-05 2019-05-08 Ansaldo Energia Switzerland AG Liner for a gas turbine combustor
EP3124749B1 (en) * 2015-07-28 2018-12-19 Ansaldo Energia Switzerland AG First stage turbine vane arrangement
GB2551181A (en) * 2016-06-09 2017-12-13 Hieta Tech Limited Radial flow turbine heat engine
WO2019003724A1 (ja) * 2017-06-29 2019-01-03 三菱日立パワーシステムズ株式会社 ガスタービンの１段静翼、ガスタービン、ガスタービンの静翼ユニット及び燃焼器アセンブリ
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

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
US4016718A (en) * 1975-07-21 1977-04-12 United Technologies Corporation Gas turbine engine having an improved transition duct support
SU1449775A1 (ru) * 1987-04-30 1989-01-07 Производственное Объединение Турбостроения "Ленинградский Металлический Завод" Выходной патрубок секционной камеры сгорани газотурбинной установки
US5402631A (en) 1991-05-10 1995-04-04 Praxair Technology, Inc. Integration of combustor-turbine units and integral-gear pressure processors
DE4446610A1 (de) 1994-12-24 1996-06-27 Abb Management Ag Verfahren zum Betrieb einer Gasturbogruppe
US6450762B1 (en) * 2001-01-31 2002-09-17 General Electric Company Integral aft seal for turbine applications
US6840048B2 (en) * 2002-09-26 2005-01-11 General Electric Company Dynamically uncoupled can combustor
US7303372B2 (en) 2005-11-18 2007-12-04 General Electric Company Methods and apparatus for cooling combustion turbine engine components
CN101965443B (zh) * 2008-02-27 2014-04-23 三菱重工业株式会社 燃气轮机及燃气轮机的机室开放方法
US8065881B2 (en) * 2008-08-12 2011-11-29 Siemens Energy, Inc. Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
US9822649B2 (en) * 2008-11-12 2017-11-21 General Electric Company Integrated combustor and stage 1 nozzle in a gas turbine and method
US8408004B2 (en) 2009-06-16 2013-04-02 General Electric Company Resonator assembly for mitigating dynamics in gas turbines
JP5479058B2 (ja) * 2009-12-07 2014-04-23 三菱重工業株式会社 燃焼器とタービン部との連通構造、および、ガスタービン
US10030872B2 (en) * 2011-02-28 2018-07-24 General Electric Company Combustor mixing joint with flow disruption surface
CH704829A2 (de) 2011-04-08 2012-11-15 Alstom Technology Ltd Gasturbogruppe und zugehöriges Betriebsverfahren.
US9249678B2 (en) * 2012-06-27 2016-02-02 General Electric Company Transition duct for a gas turbine

Also Published As

Publication number Publication date
US20140109579A1 (en) 2014-04-24
JP2014084874A (ja) 2014-05-12
RU2013146536A (ru) 2015-04-27
CN103776057A (zh) 2014-05-07
KR101576455B1 (ko) 2015-12-10
US9482106B2 (en) 2016-11-01
EP2725199A1 (en) 2014-04-30
CN103776057B (zh) 2016-10-05
RU2566867C2 (ru) 2015-10-27
JP5726268B2 (ja) 2015-05-27
CA2830683A1 (en) 2014-04-24
SA113340952B1 (ar) 2015-11-25
BR102013027397A2 (pt) 2014-12-30
KR20140052872A (ko) 2014-05-07
CA2830683C (en) 2016-02-23
EP2725199B1 (en) 2017-10-04
EP2725197A1 (en) 2014-04-30

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Legal Events

Date Code Title Description
B03A Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]
B25D Requested change of name of applicant approved

Owner name: ANSALDO ENERGIA SWITZERLAND AG (CH)

B25A Requested transfer of rights approved

Owner name: ANSALDO ENERGIA SWITZERLAND AG (CH)

B25K Entry of change of name and/or headquarter and transfer of application, patent and certificate of addition of invention: republication

Owner name: ANSALDO ENERGIA SWITZERLAND AG (CH)

B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]
B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: EM VIRTUDE DO ARQUIVAMENTO PUBLICADO NA RPI 2485 DE 21-08-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDO O ARQUIVAMENTO DO PEDIDO DE PATENTE, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.