JP2001254696A5 - - Google Patents

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Publication number
JP2001254696A5
JP2001254696A5 JP2001020890A JP2001020890A JP2001254696A5 JP 2001254696 A5 JP2001254696 A5 JP 2001254696A5 JP 2001020890 A JP2001020890 A JP 2001020890A JP 2001020890 A JP2001020890 A JP 2001020890A JP 2001254696 A5 JP2001254696 A5 JP 2001254696A5
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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.)
Granted
Application number
JP2001020890A
Other versions
JP4785256B2 (ja
JP2001254696A (ja
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Publication date
Priority claimed from US09/710,656 external-priority patent/US6375421B1/en
Application filed filed Critical
Publication of JP2001254696A publication Critical patent/JP2001254696A/ja
Publication of JP2001254696A5 publication Critical patent/JP2001254696A5/ja
Application granted granted Critical
Publication of JP4785256B2 publication Critical patent/JP4785256B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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JP2001020890A 2000-01-31 2001-01-30 ピギーバック方式のロータブリスク Expired - Fee Related JP4785256B2 (ja)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US17921200P 2000-01-31 2000-01-31
US60/179212 2000-01-31
US09/710656 2000-01-31
US09/710,656 US6375421B1 (en) 2000-01-31 2000-11-09 Piggyback rotor blisk

Publications (3)

Publication Number Publication Date
JP2001254696A JP2001254696A (ja) 2001-09-21
JP2001254696A5 true JP2001254696A5 (ja) 2008-03-13
JP4785256B2 JP4785256B2 (ja) 2011-10-05

Family

ID=26875112

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2001020890A Expired - Fee Related JP4785256B2 (ja) 2000-01-31 2001-01-30 ピギーバック方式のロータブリスク

Country Status (4)

Country Link
US (1) US6375421B1 (ja)
EP (1) EP1122443B1 (ja)
JP (1) JP4785256B2 (ja)
DE (1) DE60121642T2 (ja)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6354780B1 (en) * 2000-09-15 2002-03-12 General Electric Company Eccentric balanced blisk
DE10159669A1 (de) * 2001-12-05 2003-07-03 Rolls Royce Deutschland Bajonettverbindung für ein Ringgehäuse eines Hochdruckkompressors einer Gasturbine
GB2398882B (en) * 2003-02-27 2007-09-05 Rolls Royce Plc Rotor balancing
FR2857419B1 (fr) * 2003-07-11 2005-09-23 Snecma Moteurs Liaison amelioree entre disques aubages sur la ligne rotor d'un compresseur
US7458774B2 (en) * 2005-12-20 2008-12-02 General Electric Company High pressure turbine disk hub with curved hub surface and method
DE102006033299A1 (de) * 2006-07-17 2008-01-24 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Reparatur eines in BLISK-Bauweise ausgeführten Verdichterrotors
DE102007031712A1 (de) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung und Verfahren zum Einspannen von beschaufelten Rotorscheiben eines Strahltriebwerkes
US8215919B2 (en) * 2008-02-22 2012-07-10 Hamilton Sundstrand Corporation Curved tooth coupling for a miniature gas turbine engine
GB0814314D0 (en) * 2008-08-06 2008-09-10 Rolls Royce Plc A Method of assembling a multi-stage turbine or compressor
DE102008060571A1 (de) * 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Montagevorrichtung für ein Rotorsystem einer Axial-Strömungsmaschine
US8998588B2 (en) * 2011-08-18 2015-04-07 General Electric Company Segmented fan assembly
US8932011B2 (en) * 2011-10-06 2015-01-13 United Technologies Corporation Shaft assembly for a gas turbine engine
US8935923B2 (en) * 2011-10-25 2015-01-20 United Technologies Corporation Gas turbine engine with intercooling turbine section and intercooling turbine section bypass
US9410446B2 (en) 2012-07-10 2016-08-09 United Technologies Corporation Dynamic stability and mid axial preload control for a tie shaft coupled axial high pressure rotor
US20140064976A1 (en) * 2012-08-14 2014-03-06 Kevin L. Corcoran Rotor keyhole fillet for a gas turbine engine
US20140260326A1 (en) * 2012-10-02 2014-09-18 United Technologies Corporation Geared turbofan engine with high compressor exit temperature
US10036316B2 (en) * 2012-10-02 2018-07-31 United Technologies Corporation Geared turbofan engine with high compressor exit temperature
US10060282B2 (en) * 2014-06-10 2018-08-28 United Technologies Corporation Geared turbofan with integrally bladed rotor
FR3066552B1 (fr) * 2017-05-22 2021-11-19 Safran Aircraft Engines Assemblage sur un arbre de turbomachine d'un disque aubage monobloc et d'un rotor de compresseur basse pression a au moins deux etages d'aubes mobiles
US11231043B2 (en) 2018-02-21 2022-01-25 General Electric Company Gas turbine engine with ultra high pressure compressor
US10823191B2 (en) 2018-03-15 2020-11-03 General Electric Company Gas turbine engine arrangement with ultra high pressure compressor
US11828190B2 (en) 2021-11-18 2023-11-28 General Electric Company Airfoil joining apparatus and methods

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1047281A (ja) 1964-01-23
GB1286235A (en) 1970-01-20 1972-08-23 Rolls Royce A rotary bladed structure for a fluid flow machine
US3742706A (en) 1971-12-20 1973-07-03 Gen Electric Dual flow cooled turbine arrangement for gas turbine engines
US4016636A (en) 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
JPS5115209A (en) * 1974-07-29 1976-02-06 Hitachi Ltd Doyokunoshabanheno toritsukehohooyobi toritsukekozo
US4664599A (en) * 1985-05-01 1987-05-12 United Technologies Corporation Two stage turbine rotor assembly
FR2607866B1 (fr) 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
GB8630754D0 (en) 1986-12-23 1987-02-04 Rolls Royce Plc Turbofan gas turbine engine
JPH057903U (ja) * 1991-07-09 1993-02-02 石川島播磨重工業株式会社 部品の組付シート面補修構造
FR2712037B1 (fr) * 1993-11-03 1995-12-08 Snecma Turbomachine à compresseur dont le rotor a un étage amont amovible.
US5537814A (en) * 1994-09-28 1996-07-23 General Electric Company High pressure gas generator rotor tie rod system for gas turbine engine
US5628621A (en) * 1996-07-26 1997-05-13 General Electric Company Reinforced compressor rotor coupling

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