JP2008180219A5 - - Google Patents

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Publication number
JP2008180219A5
JP2008180219A5 JP2008007636A JP2008007636A JP2008180219A5 JP 2008180219 A5 JP2008180219 A5 JP 2008180219A5 JP 2008007636 A JP2008007636 A JP 2008007636A JP 2008007636 A JP2008007636 A JP 2008007636A JP 2008180219 A5 JP2008180219 A5 JP 2008180219A5
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JP
Japan
Prior art keywords
wing
platform
disk
cavity
stress applied
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
JP2008007636A
Other languages
English (en)
Japanese (ja)
Other versions
JP5283388B2 (ja
JP2008180219A (ja
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Publication date
Priority claimed from FR0700326A external-priority patent/FR2911632B1/fr
Application filed filed Critical
Publication of JP2008180219A publication Critical patent/JP2008180219A/ja
Publication of JP2008180219A5 publication Critical patent/JP2008180219A5/ja
Application granted granted Critical
Publication of JP5283388B2 publication Critical patent/JP5283388B2/ja
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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JP2008007636A 2007-01-18 2008-01-17 ターボ機械ファン用のロータディスク Active JP5283388B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0700326A FR2911632B1 (fr) 2007-01-18 2007-01-18 Disque de rotor de soufflante de turbomachine
FR0700326 2007-01-18

Publications (3)

Publication Number Publication Date
JP2008180219A JP2008180219A (ja) 2008-08-07
JP2008180219A5 true JP2008180219A5 (enExample) 2013-05-09
JP5283388B2 JP5283388B2 (ja) 2013-09-04

Family

ID=38421439

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2008007636A Active JP5283388B2 (ja) 2007-01-18 2008-01-17 ターボ機械ファン用のロータディスク

Country Status (6)

Country Link
US (1) US8246309B2 (enExample)
EP (1) EP1950381B1 (enExample)
JP (1) JP5283388B2 (enExample)
CA (1) CA2619299C (enExample)
FR (1) FR2911632B1 (enExample)
RU (1) RU2454572C2 (enExample)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TWM334886U (en) * 2007-12-12 2008-06-21 Taiwei Fan Technology Co Ltd Combination type miniature axial-flow fan
DE102009007468A1 (de) * 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
US8485784B2 (en) * 2009-07-14 2013-07-16 General Electric Company Turbine bucket lockwire rotation prevention
EP2299056A1 (de) * 2009-09-02 2011-03-23 Siemens Aktiengesellschaft Kühlung eines Gasturbinenbauteils ausgebildet als Rotorscheibe oder Turbinenschaufel
FR2955904B1 (fr) * 2010-02-04 2012-07-20 Snecma Soufflante de turbomachine
FR2968363B1 (fr) 2010-12-03 2014-12-05 Snecma Rotor de turbomachine avec une cale anti-usure entre un disque et un anneau
EP2546465A1 (en) 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Blade root, corresponding blade, rotor disc, and turbomachine assembly
JP2013249756A (ja) * 2012-05-31 2013-12-12 Hitachi Ltd 圧縮機
EP2971568B1 (en) * 2013-03-15 2021-11-03 Raytheon Technologies Corporation Flap seal for a fan of a gas turbine engine
CA2918320C (en) 2013-07-26 2018-05-15 Mra Systems, Inc. Aircraft engine pylon
FR3014151B1 (fr) * 2013-11-29 2015-12-04 Snecma Soufflante, en particulier pour une turbomachine
FR3064667B1 (fr) * 2017-03-31 2020-05-15 Safran Aircraft Engines Dispositif de refroidissement d'un rotor de turbomachine
CN107100894A (zh) * 2017-07-05 2017-08-29 陕西金翼通风科技有限公司 一种通风机用叶片、叶轮及叶轮的安装方法
US10830048B2 (en) 2019-02-01 2020-11-10 Raytheon Technologies Corporation Gas turbine rotor disk having scallop shield feature
EP3862571A1 (en) * 2020-02-06 2021-08-11 ABB Schweiz AG Fan, synchronous machine and method for producing a fan

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2965355A (en) * 1956-01-17 1960-12-20 United Aircraft Corp Turbine disc burst inhibitor
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
US4453890A (en) * 1981-06-18 1984-06-12 General Electric Company Blading system for a gas turbine engine
FR2519072B1 (fr) * 1981-12-29 1986-05-30 Snecma Dispositif de retenue axiale et radiale d'aube de rotor de turboreacteur
FR2695433B1 (fr) * 1992-09-09 1994-10-21 Snecma Joint annulaire d'étanchéité disposé à une extrémité axiale d'un rotor et recouvrant des brochages d'aubes.
US5281098A (en) * 1992-10-28 1994-01-25 General Electric Company Single ring blade retaining assembly
US5443365A (en) * 1993-12-02 1995-08-22 General Electric Company Fan blade for blade-out protection
RU2173390C2 (ru) * 1996-06-21 2001-09-10 Сименс Акциенгезелльшафт Ротор для турбомашины с устанавливаемыми в пазы лопатками, а также лопатка для ротора
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
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
GB9925261D0 (en) * 1999-10-27 1999-12-29 Rolls Royce Plc Locking devices
FR2803623B1 (fr) * 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
US6481971B1 (en) * 2000-11-27 2002-11-19 General Electric Company Blade spacer
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
GB2380770B (en) * 2001-10-13 2005-09-07 Rolls Royce Plc Indentor arrangement
GB2409240B (en) * 2003-12-18 2007-04-11 Rolls Royce Plc A gas turbine rotor
JP2005273646A (ja) * 2004-02-25 2005-10-06 Mitsubishi Heavy Ind Ltd 動翼体及びこの動翼体を有する回転機械
EP1703079A1 (de) * 2005-08-26 2006-09-20 Siemens Aktiengesellschaft Rotationskörper zum Befestigen von Laufschaufeln einer Strömungsmaschine

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