JP2003027962A5 - - Google Patents

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Publication number
JP2003027962A5
JP2003027962A5 JP2002125433A JP2002125433A JP2003027962A5 JP 2003027962 A5 JP2003027962 A5 JP 2003027962A5 JP 2002125433 A JP2002125433 A JP 2002125433A JP 2002125433 A JP2002125433 A JP 2002125433A JP 2003027962 A5 JP2003027962 A5 JP 2003027962A5
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JP
Japan
Prior art keywords
airfoil
trailing edge
edge chamber
cavity
tip region
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
JP2002125433A
Other languages
English (en)
Japanese (ja)
Other versions
JP4138363B2 (ja
JP2003027962A (ja
Filing date
Publication date
Priority claimed from US09/844,206 external-priority patent/US6561758B2/en
Application filed filed Critical
Publication of JP2003027962A publication Critical patent/JP2003027962A/ja
Publication of JP2003027962A5 publication Critical patent/JP2003027962A5/ja
Application granted granted Critical
Publication of JP4138363B2 publication Critical patent/JP4138363B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

JP2002125433A 2001-04-27 2002-04-26 ガスタービンエンジン、その翼形部およびその製造方法 Expired - Fee Related JP4138363B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/844206 2001-04-27
US09/844,206 US6561758B2 (en) 2001-04-27 2001-04-27 Methods and systems for cooling gas turbine engine airfoils

Publications (3)

Publication Number Publication Date
JP2003027962A JP2003027962A (ja) 2003-01-29
JP2003027962A5 true JP2003027962A5 (enExample) 2005-08-11
JP4138363B2 JP4138363B2 (ja) 2008-08-27

Family

ID=25292111

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2002125433A Expired - Fee Related JP4138363B2 (ja) 2001-04-27 2002-04-26 ガスタービンエンジン、その翼形部およびその製造方法

Country Status (4)

Country Link
US (1) US6561758B2 (enExample)
EP (1) EP1253292B1 (enExample)
JP (1) JP4138363B2 (enExample)
DE (1) DE60220967T2 (enExample)

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US7424021B2 (en) * 2003-01-31 2008-09-09 Hewlett-Packard Development Company, L.P. Method and apparatus for processing network topology data
US6902372B2 (en) * 2003-09-04 2005-06-07 Siemens Westinghouse Power Corporation Cooling system for a turbine blade
US7137780B2 (en) * 2004-06-17 2006-11-21 Siemens Power Generation, Inc. Internal cooling system for a turbine blade
EP1655451B1 (en) * 2004-11-09 2010-06-30 Rolls-Royce Plc A cooling arrangement
US7300250B2 (en) * 2005-09-28 2007-11-27 Pratt & Whitney Canada Corp. Cooled airfoil trailing edge tip exit
US7431562B2 (en) * 2005-12-21 2008-10-07 General Electric Company Method and apparatus for cooling gas turbine rotor blades
US7513738B2 (en) * 2006-02-15 2009-04-07 General Electric Company Methods and apparatus for cooling gas turbine rotor blades
US7431561B2 (en) * 2006-02-16 2008-10-07 General Electric Company Method and apparatus for cooling gas turbine rotor blades
FR2898384B1 (fr) * 2006-03-08 2011-09-16 Snecma Aube mobile de turbomachine a cavite commune d'alimentation en air de refroidissement
US20080085193A1 (en) * 2006-10-05 2008-04-10 Siemens Power Generation, Inc. Turbine airfoil cooling system with enhanced tip corner cooling channel
US7704046B1 (en) 2007-05-24 2010-04-27 Florida Turbine Technologies, Inc. Turbine blade with serpentine cooling circuit
US8172506B2 (en) * 2008-11-26 2012-05-08 General Electric Company Method and system for cooling engine components
US9890647B2 (en) * 2009-12-29 2018-02-13 Rolls-Royce North American Technologies Inc. Composite gas turbine engine component
US8584470B2 (en) 2012-02-15 2013-11-19 United Technologies Corporation Tri-lobed cooling hole and method of manufacture
US9279330B2 (en) 2012-02-15 2016-03-08 United Technologies Corporation Gas turbine engine component with converging/diverging cooling passage
US8733111B2 (en) 2012-02-15 2014-05-27 United Technologies Corporation Cooling hole with asymmetric diffuser
US8763402B2 (en) 2012-02-15 2014-07-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US9416971B2 (en) 2012-02-15 2016-08-16 United Technologies Corporation Multiple diffusing cooling hole
US8683814B2 (en) 2012-02-15 2014-04-01 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
US8850828B2 (en) 2012-02-15 2014-10-07 United Technologies Corporation Cooling hole with curved metering section
US8572983B2 (en) 2012-02-15 2013-11-05 United Technologies Corporation Gas turbine engine component with impingement and diffusive cooling
US8683813B2 (en) 2012-02-15 2014-04-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US10422230B2 (en) 2012-02-15 2019-09-24 United Technologies Corporation Cooling hole with curved metering section
US9024226B2 (en) 2012-02-15 2015-05-05 United Technologies Corporation EDM method for multi-lobed cooling hole
US9598979B2 (en) 2012-02-15 2017-03-21 United Technologies Corporation Manufacturing methods for multi-lobed cooling holes
US8707713B2 (en) 2012-02-15 2014-04-29 United Technologies Corporation Cooling hole with crenellation features
US9422815B2 (en) 2012-02-15 2016-08-23 United Technologies Corporation Gas turbine engine component with compound cusp cooling configuration
US8689568B2 (en) 2012-02-15 2014-04-08 United Technologies Corporation Cooling hole with thermo-mechanical fatigue resistance
US9416665B2 (en) 2012-02-15 2016-08-16 United Technologies Corporation Cooling hole with enhanced flow attachment
US9284844B2 (en) 2012-02-15 2016-03-15 United Technologies Corporation Gas turbine engine component with cusped cooling hole
US9410435B2 (en) 2012-02-15 2016-08-09 United Technologies Corporation Gas turbine engine component with diffusive cooling hole
US8522558B1 (en) 2012-02-15 2013-09-03 United Technologies Corporation Multi-lobed cooling hole array
US9482100B2 (en) 2012-02-15 2016-11-01 United Technologies Corporation Multi-lobed cooling hole
US9273560B2 (en) 2012-02-15 2016-03-01 United Technologies Corporation Gas turbine engine component with multi-lobed cooling hole
US9810072B2 (en) 2014-05-28 2017-11-07 General Electric Company Rotor blade cooling
US10605092B2 (en) 2016-07-11 2020-03-31 United Technologies Corporation Cooling hole with shaped meter
DE102019201085A1 (de) * 2019-01-29 2020-07-30 Siemens Aktiengesellschaft Herstellungsverfahren für ein Bauteil mit integrierten Kanälen
TWI720442B (zh) * 2019-03-20 2021-03-01 財團法人金屬工業研究發展中心 封閉式輪葉之電化學加工裝置
US11761339B2 (en) 2020-05-20 2023-09-19 Siemens Energy Global GmbH & Co. KG Turbine blade

Family Cites Families (12)

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US5360957A (en) * 1992-06-11 1994-11-01 General Electric Company Controlled apparatus for electrical discharge machining
US5660524A (en) 1992-07-13 1997-08-26 General Electric Company Airfoil blade having a serpentine cooling circuit and impingement cooling
US5599166A (en) * 1994-11-01 1997-02-04 United Technologies Corporation Core for fabrication of gas turbine engine airfoils
JP3411775B2 (ja) * 1997-03-10 2003-06-03 三菱重工業株式会社 ガスタービン動翼
JPH10280904A (ja) * 1997-04-01 1998-10-20 Mitsubishi Heavy Ind Ltd ガスタービン冷却動翼
US5813118A (en) 1997-06-23 1998-09-29 General Electric Company Method for repairing an air cooled turbine engine airfoil
US6220817B1 (en) 1997-11-17 2001-04-24 General Electric Company AFT flowing multi-tier airfoil cooling circuit
US5975851A (en) * 1997-12-17 1999-11-02 United Technologies Corporation Turbine blade with trailing edge root section cooling
US6183811B1 (en) 1998-12-15 2001-02-06 General Electric Company Method of repairing turbine airfoils
US6206638B1 (en) 1999-02-12 2001-03-27 General Electric Company Low cost airfoil cooling circuit with sidewall impingement cooling chambers
US6234753B1 (en) 1999-05-24 2001-05-22 General Electric Company Turbine airfoil with internal cooling
US6174135B1 (en) 1999-06-30 2001-01-16 General Electric Company Turbine blade trailing edge cooling openings and slots

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