JP2005061418A5 - - Google Patents

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Publication number
JP2005061418A5
JP2005061418A5 JP2004236971A JP2004236971A JP2005061418A5 JP 2005061418 A5 JP2005061418 A5 JP 2005061418A5 JP 2004236971 A JP2004236971 A JP 2004236971A JP 2004236971 A JP2004236971 A JP 2004236971A JP 2005061418 A5 JP2005061418 A5 JP 2005061418A5
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JP
Japan
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.)
Withdrawn
Application number
JP2004236971A
Other versions
JP2005061418A (ja
Filing date
Publication date
Priority claimed from US10/642,719 external-priority patent/US6848885B1/en
Application filed filed Critical
Publication of JP2005061418A publication Critical patent/JP2005061418A/ja
Publication of JP2005061418A5 publication Critical patent/JP2005061418A5/ja
Withdrawn legal-status Critical Current

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JP2004236971A 2003-08-18 2004-08-17 ガスタービンエンジンを製作するための方法及び装置 Withdrawn JP2005061418A (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/642,719 US6848885B1 (en) 2003-08-18 2003-08-18 Methods and apparatus for fabricating gas turbine engines

Publications (2)

Publication Number Publication Date
JP2005061418A JP2005061418A (ja) 2005-03-10
JP2005061418A5 true JP2005061418A5 (ja) 2007-09-27

Family

ID=34063447

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2004236971A Withdrawn JP2005061418A (ja) 2003-08-18 2004-08-17 ガスタービンエンジンを製作するための方法及び装置

Country Status (3)

Country Link
US (1) US6848885B1 (ja)
EP (1) EP1508673A3 (ja)
JP (1) JP2005061418A (ja)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE503914T1 (de) * 2004-05-17 2011-04-15 Carlton Forge Works Turbinengehäuseverstärkung bei einem gasturbinentriebwerk
US8191254B2 (en) 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US7377742B2 (en) * 2005-10-14 2008-05-27 General Electric Company Turbine shroud assembly and method for assembling a gas turbine engine
US8079773B2 (en) * 2005-10-18 2011-12-20 General Electric Company Methods and apparatus for assembling composite structures
US8197186B2 (en) * 2007-06-29 2012-06-12 General Electric Company Flange with axially extending holes for gas turbine engine clearance control
US8393855B2 (en) * 2007-06-29 2013-03-12 General Electric Company Flange with axially curved impingement surface for gas turbine engine clearance control
GB0909470D0 (en) * 2009-06-03 2009-07-15 Rolls Royce Plc A guide vane assembly
EP2900941B1 (en) * 2012-09-26 2016-12-14 United Technologies Corporation Combined high pressure turbine case and turbine intermediate case
EP3030755B1 (en) * 2013-08-07 2022-04-20 Raytheon Technologies Corporation Clearance control assembly with specific assembly of a clearance control ring
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
US9784132B2 (en) * 2015-04-20 2017-10-10 Pratt & Whitney Canada Corp. Voltage discharge channelling assembly for a gas turbine engine
EP3153671A1 (de) * 2015-10-08 2017-04-12 MTU Aero Engines GmbH Schutzvorrichtung für eine strömungsmaschine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR996476A (fr) * 1949-10-01 1951-12-19 Cem Comp Electro Mec Cylindre pour turbines à gaz
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
GB2019954B (en) * 1978-04-04 1982-08-04 Rolls Royce Turbomachine housing
US4840026A (en) * 1988-02-24 1989-06-20 The United States Of America As Represented By The Secretary Of The Air Force Band clamp apparatus
US5154575A (en) * 1991-07-01 1992-10-13 United Technologies Corporation Thermal blade tip clearance control for gas turbine engines
GB9709086D0 (en) * 1997-05-07 1997-06-25 Rolls Royce Plc Gas turbine engine cooling apparatus
US6290455B1 (en) * 1999-12-03 2001-09-18 General Electric Company Contoured hardwall containment
US6514041B1 (en) * 2001-09-12 2003-02-04 Alstom (Switzerland) Ltd Carrier for guide vane and heat shield segment

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