JP2013139789A5 - - Google Patents

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Publication number
JP2013139789A5
JP2013139789A5 JP2012280443A JP2012280443A JP2013139789A5 JP 2013139789 A5 JP2013139789 A5 JP 2013139789A5 JP 2012280443 A JP2012280443 A JP 2012280443A JP 2012280443 A JP2012280443 A JP 2012280443A JP 2013139789 A5 JP2013139789 A5 JP 2013139789A5
Authority
JP
Japan
Prior art keywords
holes
hole
turbomachine component
damping
annular
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.)
Pending
Application number
JP2012280443A
Other languages
English (en)
Japanese (ja)
Other versions
JP2013139789A (ja
Filing date
Publication date
Priority claimed from US13/343,519 external-priority patent/US8926290B2/en
Application filed filed Critical
Publication of JP2013139789A publication Critical patent/JP2013139789A/ja
Publication of JP2013139789A5 publication Critical patent/JP2013139789A5/ja
Pending legal-status Critical Current

Links

JP2012280443A 2012-01-04 2012-12-25 インペラチューブ組立体 Pending JP2013139789A (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/343,519 US8926290B2 (en) 2012-01-04 2012-01-04 Impeller tube assembly
US13/343,519 2012-01-04

Publications (2)

Publication Number Publication Date
JP2013139789A JP2013139789A (ja) 2013-07-18
JP2013139789A5 true JP2013139789A5 (enExample) 2016-02-12

Family

ID=47665817

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2012280443A Pending JP2013139789A (ja) 2012-01-04 2012-12-25 インペラチューブ組立体

Country Status (5)

Country Link
US (1) US8926290B2 (enExample)
EP (1) EP2612988A3 (enExample)
JP (1) JP2013139789A (enExample)
CN (1) CN103195746B (enExample)
RU (1) RU2615567C2 (enExample)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2787169A1 (de) * 2013-04-04 2014-10-08 MTU Aero Engines GmbH Rotor für eine Strömungsmaschine
DE102015216110A1 (de) 2015-08-24 2017-03-02 Rolls-Royce Deutschland Ltd & Co Kg Verdichter und Verfahren zur Montage eines Verdichters
FR3043131B1 (fr) * 2015-10-28 2017-11-03 Snecma Procede pour introduire un desaccordage volontaire dans une roue aubagee de turbomachine
KR101896436B1 (ko) 2017-04-12 2018-09-10 두산중공업 주식회사 보강디스크를 포함하는 압축기 및 이를 포함하는 가스터빈
CN114776927B (zh) * 2022-04-16 2024-04-09 中国航发沈阳发动机研究所 一种航空发动机引气管阻尼减振结构

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3697192A (en) * 1970-05-07 1972-10-10 United Aircraft Corp Hollow turbine blade
US4142843A (en) * 1977-03-30 1979-03-06 Murray Corporation Compressor block and tube assembly
US4314486A (en) * 1980-04-11 1982-02-09 Hellwig Lowell L Vibration dampening ring
SU1127354A1 (ru) * 1982-09-06 1996-04-10 Производственное объединение "Турбомоторный завод" Охлаждаемое рабочее колесо газовой турбины
US5472313A (en) 1991-10-30 1995-12-05 General Electric Company Turbine disk cooling system
US5267832A (en) 1992-03-30 1993-12-07 United Technologies Corporation Flarable retainer
US5423178A (en) 1992-09-28 1995-06-13 Parker-Hannifin Corporation Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
US5526640A (en) 1994-05-16 1996-06-18 Technical Directions, Inc. Gas turbine engine including a bearing support tube cantilevered from a turbine nozzle wall
US6027304A (en) 1998-05-27 2000-02-22 General Electric Co. High pressure inlet bleed heat system for the compressor of a turbine
FR2782539B1 (fr) 1998-08-20 2000-10-06 Snecma Turbomachine comportant un dispositif de fourniture de gaz pressurise
US6283712B1 (en) 1999-09-07 2001-09-04 General Electric Company Cooling air supply through bolted flange assembly
FR2825413B1 (fr) * 2001-05-31 2003-09-05 Snecma Moteurs Dispositif de prelevement d'air par ecoulement centripete
DE10159670A1 (de) 2001-12-05 2003-06-18 Rolls Royce Deutschland Wirbelgleichrichter im Hochdruckverdichter einer Gasturbine
DE10310815A1 (de) 2003-03-12 2004-09-23 Rolls-Royce Deutschland Ltd & Co Kg Wirbelgleichrichter in Röhrenbauweise mit Haltering
RU2289029C2 (ru) * 2004-02-05 2006-12-10 Государственное предприятие "Запорожское машиностроительное конструкторское бюро "Прогресс" им. акад. А.Г. Ивченко" Устройство подвода охлаждающего воздуха к рабочим лопаткам колеса турбины
DE102004006775A1 (de) 2004-02-11 2006-10-19 Rolls-Royce Deutschland Ltd & Co Kg Wirbelgleichrichter in Röhrenbauweise
DE102004042295A1 (de) 2004-09-01 2006-03-02 Mtu Aero Engines Gmbh Rotor für ein Triebwerk
FR2889565B1 (fr) 2005-08-03 2012-05-18 Snecma Compresseur a prelevement d'air centripete
DE102005040575A1 (de) * 2005-08-26 2007-03-08 Rolls-Royce Deutschland Ltd & Co Kg Wirbelgleichrichter
US7344354B2 (en) * 2005-09-08 2008-03-18 General Electric Company Methods and apparatus for operating gas turbine engines
US7870742B2 (en) 2006-11-10 2011-01-18 General Electric Company Interstage cooled turbine engine
DE102008024146A1 (de) * 2008-05-19 2009-11-26 Rolls-Royce Deutschland Ltd & Co Kg Kombinierter Wirbelgleichrichter
US8177503B2 (en) 2009-04-17 2012-05-15 United Technologies Corporation Turbine engine rotating cavity anti-vortex cascade
US8465252B2 (en) 2009-04-17 2013-06-18 United Technologies Corporation Turbine engine rotating cavity anti-vortex cascade

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