BRPI0503610A - ajuste do fluxo de ar em um componente de turbina através do depósito de uma camada metálica de revestimento - Google Patents
ajuste do fluxo de ar em um componente de turbina através do depósito de uma camada metálica de revestimentoInfo
- Publication number
- BRPI0503610A BRPI0503610A BRPI0503610-0A BRPI0503610A BRPI0503610A BR PI0503610 A BRPI0503610 A BR PI0503610A BR PI0503610 A BRPI0503610 A BR PI0503610A BR PI0503610 A BRPI0503610 A BR PI0503610A
- Authority
- BR
- Brazil
- Prior art keywords
- turbine component
- air flow
- coating layer
- metallic coating
- depositing
- Prior art date
Links
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
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
-
- 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
- F23R2900/03042—Film cooled combustion chamber walls or domes
-
- 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
- Y10T29/49339—Hollow blade
- Y10T29/49341—Hollow blade with cooling passage
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
"AJUSTE DO FLUXO DE AR EM UM COMPONENTE DE TURBINA ATRAVéS DO DEPóSITO DE UMA CAMADA METáLICA DE REVESTIMENTO". Um método para ajustar o fluxo de ar em um componente de turbina (22, 26) apresentando uma pluralidade de orifícios de fluxo de ar (122). O método compreende a etapa de depositar uma camada metálica de revestimento (130) na superfície (74, 82) do componente de turbina (22, 26) de tal forma que ao menos alguns dos orifícios de fluxo de ar (130) são parcialmente preenchidos de tal sorte que o volume dos orifícios (122) parcialmente preenchidos é alterado de tal modo a ajustar o fluxo de ar através do componente de turbina (130). Também é fornecido um componente de turbina (22, 26) apresentando uma pluralidade de orifícios de fluxo de ar (122), ao menos alguns dos orifícios de fluxo de ar (122) sendo parcialmente preenchidos com uma camada metálica de revestimento (130) para alterar o volume deste, de tal forma a ajustar o fluxo de ar através do componente de turbina (22, 26).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/934,172 US7216485B2 (en) | 2004-09-03 | 2004-09-03 | Adjusting airflow in turbine component by depositing overlay metallic coating |
Publications (1)
Publication Number | Publication Date |
---|---|
BRPI0503610A true BRPI0503610A (pt) | 2006-04-18 |
Family
ID=35427941
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BRPI0503610-0A BRPI0503610A (pt) | 2004-09-03 | 2005-08-22 | ajuste do fluxo de ar em um componente de turbina através do depósito de uma camada metálica de revestimento |
Country Status (6)
Country | Link |
---|---|
US (1) | US7216485B2 (pt) |
EP (1) | EP1632720B1 (pt) |
JP (1) | JP2006071274A (pt) |
BR (1) | BRPI0503610A (pt) |
CA (1) | CA2517080C (pt) |
SG (1) | SG120305A1 (pt) |
Families Citing this family (47)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7614235B2 (en) * | 2005-03-01 | 2009-11-10 | United Technologies Corporation | Combustor cooling hole pattern |
US7509809B2 (en) * | 2005-06-10 | 2009-03-31 | Pratt & Whitney Canada Corp. | Gas turbine engine combustor with improved cooling |
GB2429515B (en) * | 2005-08-11 | 2008-06-25 | Rolls Royce Plc | Cooling method and apparatus |
FR2892180B1 (fr) * | 2005-10-18 | 2008-02-01 | Snecma Sa | Amelioration des perfomances d'une chambre de combustion par multiperforation des parois |
US7631502B2 (en) * | 2005-12-14 | 2009-12-15 | United Technologies Corporation | Local cooling hole pattern |
US7622160B2 (en) * | 2006-07-28 | 2009-11-24 | General Electric Company | Method for concurrent thermal spray and cooling hole cleaning |
US8141370B2 (en) * | 2006-08-08 | 2012-03-27 | General Electric Company | Methods and apparatus for radially compliant component mounting |
US20080148565A1 (en) * | 2006-12-22 | 2008-06-26 | Edward John Emilianowicz | Methods for making combustor liner replacement panels |
DE102007048484A1 (de) * | 2007-10-09 | 2009-04-16 | Man Turbo Ag | Heißgasgeführte Komponente einer Strömungsmaschine |
US8256223B2 (en) * | 2007-10-16 | 2012-09-04 | United Technologies Corporation | Ceramic combustor liner panel for a gas turbine engine |
US20090142548A1 (en) * | 2007-10-18 | 2009-06-04 | David Bruce Patterson | Air cooled gas turbine components and methods of manufacturing and repairing the same |
FR2922630B1 (fr) * | 2007-10-22 | 2015-11-13 | Snecma | Paroi de chambre de combustion a dilution et refroidissement optimises,chambre de combustion et turbomachine en etant munies |
US20100281868A1 (en) * | 2007-12-28 | 2010-11-11 | General Electric Company | Gas turbine engine combuster |
US8307657B2 (en) * | 2009-03-10 | 2012-11-13 | General Electric Company | Combustor liner cooling system |
US20100329887A1 (en) * | 2009-06-26 | 2010-12-30 | Andy Eifert | Coolable gas turbine engine component |
US9890647B2 (en) * | 2009-12-29 | 2018-02-13 | Rolls-Royce North American Technologies Inc. | Composite gas turbine engine component |
JP5578864B2 (ja) * | 2010-01-20 | 2014-08-27 | 三菱重工業株式会社 | 流路付き壁部材の補修方法 |
EP2444590B1 (de) * | 2010-10-19 | 2014-08-06 | Siemens Aktiengesellschaft | Verfahren zur Beschichtung von Kühlbohrungen |
US8673397B2 (en) * | 2010-11-10 | 2014-03-18 | General Electric Company | Methods of fabricating and coating a component |
JP5726545B2 (ja) * | 2011-01-24 | 2015-06-03 | 株式会社東芝 | トランジションピースの損傷補修方法およびトランジションピース |
US10113435B2 (en) * | 2011-07-15 | 2018-10-30 | United Technologies Corporation | Coated gas turbine components |
FR2981733B1 (fr) * | 2011-10-25 | 2013-12-27 | Snecma | Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci |
FR2982008B1 (fr) * | 2011-10-26 | 2013-12-13 | Snecma | Paroi annulaire de chambre de combustion a refroidissement ameliore au niveau des trous primaires et de dilution |
US9175402B2 (en) * | 2012-07-30 | 2015-11-03 | General Electric Company | Turbine repair process, repaired coating, and repaired turbine component |
US10060630B2 (en) * | 2012-10-01 | 2018-08-28 | Ansaldo Energia Ip Uk Limited | Flamesheet combustor contoured liner |
IN2015DN03238A (pt) * | 2012-10-24 | 2015-10-02 | Alstom Technology Ltd | |
EP2735796B1 (en) * | 2012-11-23 | 2020-01-01 | Ansaldo Energia IP UK Limited | Wall of a hot gas path component of a gas turbine and method for enhancing operational behaviour of a gas turbine |
US20140157783A1 (en) * | 2012-12-10 | 2014-06-12 | General Electric Company | System for Protecting an Inner Wall of a Combustor |
US20140174091A1 (en) * | 2012-12-21 | 2014-06-26 | United Technologies Corporation | Repair procedure for a gas turbine engine via variable polarity welding |
US9879861B2 (en) | 2013-03-15 | 2018-01-30 | Rolls-Royce Corporation | Gas turbine engine with improved combustion liner |
WO2014143209A1 (en) | 2013-03-15 | 2014-09-18 | Rolls-Royce Corporation | Gas turbine engine combustor liner |
WO2015065587A1 (en) * | 2013-11-04 | 2015-05-07 | United Technologies Corporation | Coated cooling passage |
US10317080B2 (en) | 2013-12-06 | 2019-06-11 | United Technologies Corporation | Co-swirl orientation of combustor effusion passages for gas turbine engine combustor |
US10934853B2 (en) | 2014-07-03 | 2021-03-02 | Rolls-Royce Corporation | Damage tolerant cooling of high temperature mechanical system component including a coating |
WO2016099805A2 (en) * | 2014-11-21 | 2016-06-23 | General Electric Technology Gmbh | Flamesheet combustor contoured liner |
US10132498B2 (en) * | 2015-01-20 | 2018-11-20 | United Technologies Corporation | Thermal barrier coating of a combustor dilution hole |
JP6551892B2 (ja) * | 2015-02-18 | 2019-07-31 | エムアールエイ・システムズ・エルエルシー | 音響ライナーおよび音響ライナーの入口を成形する方法 |
US10670267B2 (en) * | 2015-08-14 | 2020-06-02 | Raytheon Technologies Corporation | Combustor hole arrangement for gas turbine engine |
US10472972B2 (en) * | 2015-12-01 | 2019-11-12 | General Electric Company | Thermal management of CMC articles having film holes |
US10041677B2 (en) | 2015-12-17 | 2018-08-07 | General Electric Company | Combustion liner for use in a combustor assembly and method of manufacturing |
JP6026028B1 (ja) * | 2016-03-10 | 2016-11-16 | 三菱日立パワーシステムズ株式会社 | 燃焼器用パネル、燃焼器、燃焼装置、ガスタービン、及び燃焼器用パネルの冷却方法 |
US10443395B2 (en) | 2016-03-18 | 2019-10-15 | General Electric Company | Component for a turbine engine with a film hole |
DE102016219424A1 (de) * | 2016-10-06 | 2018-04-12 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammeranordnung einer Gasturbine sowie Fluggasturbine |
FR3080168B1 (fr) * | 2018-04-13 | 2020-03-20 | Safran Aircraft Engines | Ensemble pour une chambre de combustion de turbomachine |
US10815783B2 (en) | 2018-05-24 | 2020-10-27 | General Electric Company | In situ engine component repair |
US11407067B2 (en) | 2018-06-29 | 2022-08-09 | Pratt & Whitney Canada Corp. | Method for repairing a part |
US11585224B2 (en) | 2020-08-07 | 2023-02-21 | General Electric Company | Gas turbine engines and methods associated therewith |
Family Cites Families (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4338360A (en) * | 1980-05-01 | 1982-07-06 | General Motors Corporation | Method for coating porous metal structure |
US4743462A (en) * | 1986-07-14 | 1988-05-10 | United Technologies Corporation | Method for preventing closure of cooling holes in hollow, air cooled turbine engine components during application of a plasma spray coating |
US5724816A (en) * | 1996-04-10 | 1998-03-10 | General Electric Company | Combustor for a gas turbine with cooling structure |
US5771577A (en) * | 1996-05-17 | 1998-06-30 | General Electric Company | Method for making a fluid cooled article with protective coating |
US5822853A (en) * | 1996-06-24 | 1998-10-20 | General Electric Company | Method for making cylindrical structures with cooling channels |
US5902647A (en) * | 1996-12-03 | 1999-05-11 | General Electric Company | Method for protecting passage holes in a metal-based substrate from becoming obstructed, and related compositions |
US6042879A (en) * | 1997-07-02 | 2000-03-28 | United Technologies Corporation | Method for preparing an apertured article to be recoated |
US6365013B1 (en) * | 1997-11-03 | 2002-04-02 | Siemens Aktiengesellschaft | Coating method and device |
GB9723762D0 (en) * | 1997-11-12 | 1998-01-07 | Rolls Royce Plc | A method of coating a component |
US6145319A (en) * | 1998-07-16 | 2000-11-14 | General Electric Company | Transitional multihole combustion liner |
US6210488B1 (en) * | 1998-12-30 | 2001-04-03 | General Electric Company | Method of removing a thermal barrier coating |
US6480629B1 (en) * | 1999-04-06 | 2002-11-12 | Koninklijke Philips Electronics N.V. | Motion estimation method using orthogonal-sum block matching |
DE69911948T2 (de) * | 1999-08-09 | 2004-11-04 | Alstom Technology Ltd | Verfahren zum Verschliessen von Kühlungsöffnungen eines Gasturbinebauteils |
SG127668A1 (en) * | 1999-11-24 | 2006-12-29 | Gen Electric | Method for thermal barrier coating |
US6368060B1 (en) * | 2000-05-23 | 2002-04-09 | General Electric Company | Shaped cooling hole for an airfoil |
EP1160352B1 (en) * | 2000-05-31 | 2009-04-22 | ALSTOM Technology Ltd | Method of adjusting the size of cooling holes of a gas turbine component |
US6408610B1 (en) * | 2000-07-18 | 2002-06-25 | General Electric Company | Method of adjusting gas turbine component cooling air flow |
US6339879B1 (en) * | 2000-08-29 | 2002-01-22 | General Electric Company | Method of sizing and forming a cooling hole in a gas turbine engine component |
US6408629B1 (en) | 2000-10-03 | 2002-06-25 | General Electric Company | Combustor liner having preferentially angled cooling holes |
US6434823B1 (en) * | 2000-10-10 | 2002-08-20 | General Electric Company | Method for repairing a coated article |
US6573474B1 (en) * | 2000-10-18 | 2003-06-03 | Chromalloy Gas Turbine Corporation | Process for drilling holes through a thermal barrier coating |
US6551061B2 (en) * | 2001-03-27 | 2003-04-22 | General Electric Company | Process for forming micro cooling channels inside a thermal barrier coating system without masking material |
US6499949B2 (en) * | 2001-03-27 | 2002-12-31 | Robert Edward Schafrik | Turbine airfoil trailing edge with micro cooling channels |
US6620457B2 (en) * | 2001-07-13 | 2003-09-16 | General Electric Company | Method for thermal barrier coating and a liner made using said method |
US6513331B1 (en) * | 2001-08-21 | 2003-02-04 | General Electric Company | Preferential multihole combustor liner |
US7204019B2 (en) * | 2001-08-23 | 2007-04-17 | United Technologies Corporation | Method for repairing an apertured gas turbine component |
US6663919B2 (en) * | 2002-03-01 | 2003-12-16 | General Electric Company | Process of removing a coating deposit from a through-hole in a component and component processed thereby |
US6749396B2 (en) * | 2002-06-17 | 2004-06-15 | General Electric Company | Failsafe film cooled wall |
US6847004B2 (en) * | 2003-01-10 | 2005-01-25 | General Electric Company | Process of removing a ceramic coating deposit in a surface hole of a component |
US6723951B1 (en) * | 2003-06-04 | 2004-04-20 | Siemens Westinghouse Power Corporation | Method for reestablishing holes in a component |
US20050220618A1 (en) * | 2004-03-31 | 2005-10-06 | General Electric Company | Counter-bored film-cooling holes and related method |
-
2004
- 2004-09-03 US US10/934,172 patent/US7216485B2/en active Active
-
2005
- 2005-08-22 BR BRPI0503610-0A patent/BRPI0503610A/pt not_active Application Discontinuation
- 2005-08-25 CA CA2517080A patent/CA2517080C/en not_active Expired - Fee Related
- 2005-08-29 SG SG200505530A patent/SG120305A1/en unknown
- 2005-08-31 JP JP2005250507A patent/JP2006071274A/ja active Pending
- 2005-09-01 EP EP05255346.8A patent/EP1632720B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
CA2517080C (en) | 2013-10-08 |
CA2517080A1 (en) | 2006-03-03 |
US7216485B2 (en) | 2007-05-15 |
SG120305A1 (en) | 2006-03-28 |
JP2006071274A (ja) | 2006-03-16 |
US20060059918A1 (en) | 2006-03-23 |
EP1632720B1 (en) | 2014-04-02 |
EP1632720A1 (en) | 2006-03-08 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B07A | Technical examination (opinion): publication of technical examination (opinion) [chapter 7.1 patent gazette] | ||
B09B | Patent application refused [chapter 9.2 patent gazette] | ||
B09B | Patent application refused [chapter 9.2 patent gazette] |
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