JP2004138067A5 - - Google Patents

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Publication number
JP2004138067A5
JP2004138067A5 JP2003357147A JP2003357147A JP2004138067A5 JP 2004138067 A5 JP2004138067 A5 JP 2004138067A5 JP 2003357147 A JP2003357147 A JP 2003357147A JP 2003357147 A JP2003357147 A JP 2003357147A JP 2004138067 A5 JP2004138067 A5 JP 2004138067A5
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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.)
Pending
Application number
JP2003357147A
Other versions
JP2004138067A (ja
Filing date
Publication date
Priority claimed from US10/065,453 external-priority patent/US6769877B2/en
Application filed filed Critical
Publication of JP2004138067A publication Critical patent/JP2004138067A/ja
Publication of JP2004138067A5 publication Critical patent/JP2004138067A5/ja
Pending legal-status Critical Current

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JP2003357147A 2002-10-18 2003-10-17 圧縮機ブレードのアンダカットされた前縁及び関連する方法 Pending JP2004138067A (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/065,453 US6769877B2 (en) 2002-10-18 2002-10-18 Undercut leading edge for compressor blades and related method

Publications (2)

Publication Number Publication Date
JP2004138067A JP2004138067A (ja) 2004-05-13
JP2004138067A5 true JP2004138067A5 (ja) 2006-11-30

Family

ID=32041320

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2003357147A Pending JP2004138067A (ja) 2002-10-18 2003-10-17 圧縮機ブレードのアンダカットされた前縁及び関連する方法

Country Status (4)

Country Link
US (1) US6769877B2 (ja)
EP (1) EP1411208B1 (ja)
JP (1) JP2004138067A (ja)
KR (1) KR100847942B1 (ja)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6902376B2 (en) * 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7121803B2 (en) * 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US20040213672A1 (en) * 2003-04-25 2004-10-28 Gautreau James Charles Undercut leading edge for compressor blades and related method
FR2851285B1 (fr) * 2003-02-13 2007-03-16 Snecma Moteurs Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US7156621B2 (en) * 2004-05-14 2007-01-02 Pratt & Whitney Canada Corp. Blade fixing relief mismatch
US7549846B2 (en) * 2005-08-03 2009-06-23 United Technologies Corporation Turbine blades
FR2896289B1 (fr) * 2006-01-13 2008-03-28 Snecma Sa Masselotte d'equilibrage, disque de rotor en etant equipe, rotor et moteur d'aeronef les comportant
US7594799B2 (en) * 2006-09-13 2009-09-29 General Electric Company Undercut fillet radius for blade dovetails
US20090297351A1 (en) * 2008-05-28 2009-12-03 General Electric Company Compressor rotor blade undercut
US8834123B2 (en) * 2009-12-29 2014-09-16 Rolls-Royce Corporation Turbomachinery component
FR2963383B1 (fr) * 2010-07-27 2016-09-09 Snecma Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube
US8813331B2 (en) 2011-03-29 2014-08-26 General Electric Company Process of preparing a turbine rotor wheel, a repair wheel for a turbine rotor wheel, and a turbine rotor wheel
GB201203303D0 (en) * 2012-02-27 2012-04-11 Rolls Royce Plc Balancing of rotor
US9617860B2 (en) 2012-12-20 2017-04-11 United Technologies Corporation Fan blades for gas turbine engines with reduced stress concentration at leading edge
EP2853686A1 (de) * 2013-09-27 2015-04-01 Siemens Aktiengesellschaft Turbinenschaufel, und zugehörige Herstellungsverfahren, Stator, Rotor, Turbine und Kraftwerksanlage
US10450872B2 (en) 2016-11-08 2019-10-22 Rolls-Royce Corporation Undercut on airfoil coversheet support member

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GB791751A (en) * 1954-01-06 1958-03-12 Bristol Aero Engines Ltd Improvements in or relating to blades for axial flow gas turbine engines, and to methods of making such blades
US2913221A (en) 1955-12-12 1959-11-17 Gen Electric Damping turbine buckets
GB904546A (en) * 1958-03-17 1962-08-29 Rolls Royce Improvements in or relating to rotor blades of turbines and compressors
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
US3846041A (en) * 1972-10-31 1974-11-05 Avco Corp Impingement cooled turbine blades and method of making same
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
JPS5776208A (en) 1980-10-30 1982-05-13 Toshiba Corp Turbine vane
CH660207A5 (en) 1983-06-29 1987-03-31 Bbc Brown Boveri & Cie Device for the damping of blade vibrations in axial flow turbo engines
US4682935A (en) 1983-12-12 1987-07-28 General Electric Company Bowed turbine blade
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US5256035A (en) * 1992-06-01 1993-10-26 United Technologies Corporation Rotor blade retention and sealing construction
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US5387086A (en) * 1993-07-19 1995-02-07 General Electric Company Gas turbine blade with improved cooling
FR2716931B1 (fr) * 1994-03-03 1996-04-05 Snecma Système d'équilibrage et d'amortissement d'un dique de turbomachine.
US5536143A (en) 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
US5573377A (en) 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
JP2000512707A (ja) 1996-06-21 2000-09-26 シーメンス アクチエンゲゼルシヤフト 溝内に装着可能な翼を有するタービン機械のロータ及びロータの翼
JP3462695B2 (ja) 1997-03-12 2003-11-05 三菱重工業株式会社 ガスタービン動翼シール板
US5924843A (en) 1997-05-21 1999-07-20 General Electric Company Turbine blade cooling
US6033185A (en) 1998-09-28 2000-03-07 General Electric Company Stress relieved dovetail
US6095750A (en) 1998-12-21 2000-08-01 General Electric Company Turbine nozzle assembly
US6190131B1 (en) 1999-08-31 2001-02-20 General Electric Co. Non-integral balanced coverplate and coverplate centering slot for a turbine
JP2001271603A (ja) 2000-03-24 2001-10-05 Mitsubishi Heavy Ind Ltd ガスタービン動翼
CA2334071C (en) * 2000-02-23 2005-05-24 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade
US6419753B1 (en) 2000-04-07 2002-07-16 General Electric Company Apparatus and method for masking multiple turbine components
US6402471B1 (en) 2000-11-03 2002-06-11 General Electric Company Turbine blade for gas turbine engine and method of cooling same
US6457942B1 (en) 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
US6439851B1 (en) 2000-12-21 2002-08-27 United Technologies Corporation Reduced stress rotor blade and disk assembly
US6478537B2 (en) 2001-02-16 2002-11-12 Siemens Westinghouse Power Corporation Pre-segmented squealer tip for turbine blades

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