BR0200305A - Segmento de bocal de turbina e método para reparar a mesma - Google Patents

Segmento de bocal de turbina e método para reparar a mesma

Info

Publication number
BR0200305A
BR0200305A BR0200305-8A BR0200305A BR0200305A BR 0200305 A BR0200305 A BR 0200305A BR 0200305 A BR0200305 A BR 0200305A BR 0200305 A BR0200305 A BR 0200305A
Authority
BR
Brazil
Prior art keywords
reed
protrusion
turbine nozzle
nozzle segment
repairing
Prior art date
Application number
BR0200305-8A
Other languages
English (en)
Other versions
BR0200305B1 (pt
Inventor
Wayne Ray Grady
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BR0200305A publication Critical patent/BR0200305A/pt
Publication of BR0200305B1 publication Critical patent/BR0200305B1/pt

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

"SEGMENTO DE BOCAL DE TURBINA E MéTODO PARA REPARAR A MESMA". Um método para reparar um segmento de bocal de turbina (10) tendo pelo menos duas palhetas (12) dispostas entre as faixas externa e interna (14, 16) inclui separar as faixas externa e interna (14, 16) das palhetas (12), e formar uma fenda (36) para cada palheta (12) através da faixa externa (14) e uma fenda (32) para cada palheta (12) através da faixa interna (16). Uma palheta de reposição recém-fabricada (38) é provida para cada uma das palhetas originais (12). Cada palheta de reposição (38) tem uma saliência externa (48) formada em uma extremidade externa (44) dela e uma saliência interna (50) formada em uma extremidade interna (46) dela. Então, cada saliência externa (48) é inserida em uma correspondente das fendas da faixa interna (36), e cada saliência interna (50) é inserida em uma correspondente das fendas (32) da faixa interna. Uma vez que as peças estão montadas, cada saliência externa (48) é soldada à palheta externa (14) no lado frio (18), e cada saliência interna (50) é soldada à faixa interna (16) no lado frio (24). Cada palheta de reposição (38) é também soldada a forte às faixas externa e interna (14, 16) nos respectivos lados quentes (20, 26) delas.
BRPI0200305-8A 2001-01-29 2002-01-29 segmento de bocal de turbina e método para reparar a mesma. BR0200305B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/771,855 US6494677B1 (en) 2001-01-29 2001-01-29 Turbine nozzle segment and method of repairing same

Publications (2)

Publication Number Publication Date
BR0200305A true BR0200305A (pt) 2002-10-29
BR0200305B1 BR0200305B1 (pt) 2011-01-25

Family

ID=25093150

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0200305-8A BR0200305B1 (pt) 2001-01-29 2002-01-29 segmento de bocal de turbina e método para reparar a mesma.

Country Status (7)

Country Link
US (1) US6494677B1 (pt)
EP (1) EP1227218B1 (pt)
BR (1) BR0200305B1 (pt)
CA (1) CA2368289C (pt)
DE (1) DE60211228T2 (pt)
MY (1) MY127549A (pt)
SG (1) SG98472A1 (pt)

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US6793457B2 (en) * 2002-11-15 2004-09-21 General Electric Company Fabricated repair of cast nozzle
US6905308B2 (en) * 2002-11-20 2005-06-14 General Electric Company Turbine nozzle segment and method of repairing same
US6932568B2 (en) * 2003-02-27 2005-08-23 General Electric Company Turbine nozzle segment cantilevered mount
US6969233B2 (en) * 2003-02-27 2005-11-29 General Electric Company Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity
US7008185B2 (en) * 2003-02-27 2006-03-07 General Electric Company Gas turbine engine turbine nozzle bifurcated impingement baffle
FR2856749B1 (fr) * 2003-06-30 2005-09-23 Snecma Moteurs Redresseur de compresseur de moteur aeronautique a aubes collees
US7229245B2 (en) * 2004-07-14 2007-06-12 Power Systems Mfg., Llc Vane platform rail configuration for reduced airfoil stress
US7442006B2 (en) * 2005-08-15 2008-10-28 Honeywell International Inc. Integral diffuser and deswirler with continuous flow path deflected at assembly
US7413400B2 (en) * 2005-09-12 2008-08-19 Pratt & Whitney Canada Corp. Vane assembly with grommet
US7637718B2 (en) * 2005-09-12 2009-12-29 Pratt & Whitney Canada Corp. Vane assembly with outer grommets
US7530782B2 (en) * 2005-09-12 2009-05-12 Pratt & Whitney Canada Corp. Foreign object damage resistant vane assembly
US7628578B2 (en) * 2005-09-12 2009-12-08 Pratt & Whitney Canada Corp. Vane assembly with improved vane roots
US7536783B2 (en) * 2005-10-13 2009-05-26 Siemens Energy, Inc. Turbine vane airfoil reconfiguration method
US7762761B2 (en) * 2005-11-30 2010-07-27 General Electric Company Methods and apparatus for assembling turbine nozzles
DE102006016703A1 (de) * 2006-04-08 2007-10-11 Mtu Aero Engines Gmbh Verfahren zur Reparatur eines Leitschaufelsegments
US20070274854A1 (en) * 2006-05-23 2007-11-29 General Electric Company Method of making metallic composite foam components
US7845549B2 (en) * 2006-05-31 2010-12-07 General Electric Company MIM braze preforms
US20070295785A1 (en) * 2006-05-31 2007-12-27 General Electric Company Microwave brazing using mim preforms
EP1895105A1 (de) * 2006-08-30 2008-03-05 Siemens Aktiengesellschaft Verfahren zum Kühlen von Turbinenschaufeln eines Schaufelkranzes sowie Turbinenschaufelsegment für einen Turbinenschaufelkranz mit mindestens zwei aerodynamisch profilierten Schaufelblättern
WO2008094221A1 (en) * 2006-09-26 2008-08-07 Pas Technologies Inc. Method of repairing a stationary airfoil array directing three-dimensional flow
DE102006050907A1 (de) * 2006-10-28 2008-05-15 Man Turbo Ag Leitvorrichtung einer Strömungsmaschine sowie Leitschaufel für eine derartige Leitvorrichtung
US7771164B2 (en) * 2006-12-18 2010-08-10 General Electric Company Method and system for assembling a turbine engine
US9527169B2 (en) * 2007-02-27 2016-12-27 Siemens Energy, Inc. Process and apparatus for cooling a metal part during a welding operation
US20080267775A1 (en) * 2007-04-30 2008-10-30 General Electric Company Nozzle segments and method of repairing the same
US8186056B2 (en) * 2007-06-28 2012-05-29 Siemens Energy, Inc. Turbine vane restoration system
US8210807B2 (en) * 2008-08-28 2012-07-03 United Technologies Corporation Gas turbine airfoil assemblies and methods of repair
US8083465B2 (en) * 2008-09-05 2011-12-27 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
DE102008047043A1 (de) * 2008-09-13 2010-03-18 Mtu Aero Engines Gmbh Ersatzteil für eine Gasturbinen-Schaufel einer Gasturbine, Gasturbinen-Schaufel sowie ein Verfahren zur Reparatur einer Gasturbinen-Schaufel
US8162603B2 (en) * 2009-01-30 2012-04-24 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof
FR2964411B1 (fr) * 2010-09-06 2012-08-24 Messier Dowty Sa Aube de turboreacteur, notamment une aube de redresseur, et turboreacteur recevant de telles aubes
US8696311B2 (en) 2011-03-29 2014-04-15 Pratt & Whitney Canada Corp. Apparatus and method for gas turbine engine vane retention
US9045984B2 (en) * 2012-05-31 2015-06-02 United Technologies Corporation Stator vane mistake proofing
WO2014138147A2 (en) * 2013-03-07 2014-09-12 United Technologies Corporation Structural guide vane for gas turbine engine
EP2937516B1 (fr) * 2014-04-24 2020-04-01 Safran Aero Boosters SA Carter cintré monobloc de compresseur de turbomachine axiale et procédé de fabrication associé
JP5717904B1 (ja) * 2014-08-04 2015-05-13 三菱日立パワーシステムズ株式会社 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法
BE1022513B1 (fr) * 2014-11-18 2016-05-19 Techspace Aero S.A. Virole interne de compresseur de turbomachine axiale
KR101937586B1 (ko) * 2017-09-12 2019-01-10 두산중공업 주식회사 베인 조립체, 터빈 및 이를 포함하는 가스터빈
CN110953022B (zh) * 2019-11-25 2022-05-10 东方电气集团东方汽轮机有限公司 一种汽轮机喷嘴组及六弧段全周进汽式喷嘴结构
FR3111163B1 (fr) 2020-06-04 2022-06-10 Safran Aircraft Engines Distributeur de turbine pour une turbomachine
JP7284737B2 (ja) * 2020-08-06 2023-05-31 三菱重工業株式会社 ガスタービン静翼
GB202202610D0 (en) * 2022-02-25 2022-04-13 Rolls Royce Plc Casing assembly for gas turbine engine
US12180859B2 (en) * 2023-02-01 2024-12-31 Ge Infrastructure Technology Llc Nozzle segment for use with multiple different turbine engines
US12253003B1 (en) * 2023-08-21 2025-03-18 Rtx Corporation Integral stator vane weld shield

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US3802046A (en) * 1972-01-27 1974-04-09 Chromalloy American Corp Method of making or reconditioning a turbine-nozzle or the like assembly
CA989153A (en) * 1972-08-22 1976-05-18 John M. Aartman Guide vane repair
US5269057A (en) 1991-12-24 1993-12-14 Freedom Forge Corporation Method of making replacement airfoil components
US5248240A (en) 1993-02-08 1993-09-28 General Electric Company Turbine stator vane assembly
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US6173491B1 (en) * 1999-08-12 2001-01-16 Chromalloy Gas Turbine Corporation Method for replacing a turbine vane airfoil

Also Published As

Publication number Publication date
BR0200305B1 (pt) 2011-01-25
DE60211228D1 (de) 2006-06-14
CA2368289C (en) 2009-07-07
EP1227218A2 (en) 2002-07-31
EP1227218A3 (en) 2004-01-02
CA2368289A1 (en) 2002-07-29
SG98472A1 (en) 2003-09-19
US6494677B1 (en) 2002-12-17
DE60211228T2 (de) 2007-02-15
EP1227218B1 (en) 2006-05-10
MY127549A (en) 2006-12-29

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Legal Events

Date Code Title Description
B03H Publication of an application: rectification [chapter 3.8 patent gazette]

Free format text: REFERENTE A RPI 1660 DE 29/10/2002, QUANTO AO ITEM (30).

B06A Notification to applicant to reply to the report for non-patentability or inadequacy of the application [chapter 6.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 29/01/2002, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time
B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2447 DE 28-11-2017 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.