JPH11141307A5 - - Google Patents

Info

Publication number
JPH11141307A5
JPH11141307A5 JP1998260997A JP26099798A JPH11141307A5 JP H11141307 A5 JPH11141307 A5 JP H11141307A5 JP 1998260997 A JP1998260997 A JP 1998260997A JP 26099798 A JP26099798 A JP 26099798A JP H11141307 A5 JPH11141307 A5 JP H11141307A5
Authority
JP
Japan
Prior art keywords
rotor stage
excitation force
speed regions
frequency
natural frequency
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
JP1998260997A
Other languages
English (en)
Japanese (ja)
Other versions
JPH11141307A (ja
Filing date
Publication date
Priority claimed from US08/920,493 external-priority patent/US6055805A/en
Application filed filed Critical
Publication of JPH11141307A publication Critical patent/JPH11141307A/ja
Publication of JPH11141307A5 publication Critical patent/JPH11141307A5/ja
Pending legal-status Critical Current

Links

JP10260997A 1997-08-29 1998-08-31 ガスタービンエンジンのロータ段の振動を制御する装置 Pending JPH11141307A (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/920,493 1997-08-29
US08/920,493 US6055805A (en) 1997-08-29 1997-08-29 Active rotor stage vibration control

Publications (2)

Publication Number Publication Date
JPH11141307A JPH11141307A (ja) 1999-05-25
JPH11141307A5 true JPH11141307A5 (enExample) 2005-10-27

Family

ID=25443842

Family Applications (1)

Application Number Title Priority Date Filing Date
JP10260997A Pending JPH11141307A (ja) 1997-08-29 1998-08-31 ガスタービンエンジンのロータ段の振動を制御する装置

Country Status (5)

Country Link
US (2) US6055805A (enExample)
EP (2) EP1353039B1 (enExample)
JP (1) JPH11141307A (enExample)
KR (1) KR100539037B1 (enExample)
DE (2) DE69836154T2 (enExample)

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US7617670B2 (en) * 2006-03-31 2009-11-17 Lockheed Martin Corporation Flow control redistribution to mitigate high cycle fatigue
US20070245708A1 (en) * 2006-04-20 2007-10-25 United Technologies Corporation High cycle fatigue management for gas turbine engines
US7797944B2 (en) * 2006-10-20 2010-09-21 United Technologies Corporation Gas turbine engine having slim-line nacelle
US7870721B2 (en) * 2006-11-10 2011-01-18 United Technologies Corporation Gas turbine engine providing simulated boundary layer thickness increase
US7811050B2 (en) * 2006-12-28 2010-10-12 General Electric Company Operating line control of a compression system with flow recirculation
US8408491B2 (en) * 2007-04-24 2013-04-02 United Technologies Corporation Nacelle assembly having inlet airfoil for a gas turbine engine
DE102007026455A1 (de) * 2007-06-05 2008-12-11 Rolls-Royce Deutschland Ltd & Co Kg Strahltriebwerk mit Verdichterluftzirkulation und Verfahren zum Betreiben desselben
US8082726B2 (en) * 2007-06-26 2011-12-27 United Technologies Corporation Tangential anti-swirl air supply
US8402739B2 (en) * 2007-06-28 2013-03-26 United Technologies Corporation Variable shape inlet section for a nacelle assembly of a gas turbine engine
US8371806B2 (en) * 2007-10-03 2013-02-12 United Technologies Corporation Gas turbine engine having core auxiliary duct passage
US8240120B2 (en) * 2007-10-25 2012-08-14 United Technologies Corporation Vibration management for gas turbine engines
US9004399B2 (en) 2007-11-13 2015-04-14 United Technologies Corporation Nacelle flow assembly
US8186942B2 (en) * 2007-12-14 2012-05-29 United Technologies Corporation Nacelle assembly with turbulators
US8192147B2 (en) * 2007-12-14 2012-06-05 United Technologies Corporation Nacelle assembly having inlet bleed
DE102008016800A1 (de) * 2008-04-02 2009-10-08 Mtu Aero Engines Gmbh Gasturbinenverdichter
FR2931906B1 (fr) * 2008-05-30 2017-06-02 Snecma Compresseur de turbomachine avec un systeme d'injection d'air.
DE102008052409A1 (de) 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit saugseitennaher Randenergetisierung
US8591166B2 (en) * 2008-12-31 2013-11-26 Rolls-Royce North American Technologies, Inc. Axial compressor vane
DE102009032549A1 (de) * 2009-07-10 2011-01-13 Mtu Aero Engines Gmbh Verfahren zum Mindern von Schwingungsamplituden
US20110250046A1 (en) * 2010-04-07 2011-10-13 Honeywell International Inc. Turbofan engine performance recovery system and method
US8105039B1 (en) 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper
WO2013102098A1 (en) * 2011-12-29 2013-07-04 Rolls-Royce North American Technologies, Inc. Vavle for gas turbine engine
US8640820B2 (en) * 2012-01-11 2014-02-04 Polytechnic Institute Of New York University High-speed jet noise reduction via fluidic injection
US10107191B2 (en) * 2012-02-29 2018-10-23 United Technologies Corporation Geared gas turbine engine with reduced fan noise
US9017033B2 (en) 2012-06-07 2015-04-28 United Technologies Corporation Fan blade platform
EP2904252B2 (en) * 2012-10-01 2020-11-25 United Technologies Corporation Static guide vane with internal hollow channels
US20160258440A1 (en) * 2015-03-02 2016-09-08 Rolls-Royce Corporation Gas turbine engine with airfoil dampening system
FR3034145B1 (fr) * 2015-03-26 2017-04-07 Snecma Etage de compresseur
EP3296573A1 (en) * 2016-09-20 2018-03-21 Siemens Aktiengesellschaft A technique for controlling rotating stall in compressor for a gas turbine engine
CN110268197B (zh) * 2017-02-08 2020-08-14 西门子股份公司 最小化在特定频率范围内作用在涡轮叶片上的力的方法
US10775269B2 (en) * 2017-02-08 2020-09-15 Raytheon Technologies Corporation Blade health inspection using an excitation actuator and vibration sensor
EP3477120A1 (en) * 2017-10-26 2019-05-01 Siemens Aktiengesellschaft Gas turbine engine control method and system
JP6916755B2 (ja) * 2018-03-09 2021-08-11 三菱重工業株式会社 回転機械
FR3079552B1 (fr) * 2018-03-29 2021-06-04 Safran Aircraft Engines Turbomachine comportant au moins une aube amont comportant une portion de soufflage pour limiter la resonance d'une aube aval
US20200072062A1 (en) * 2018-08-31 2020-03-05 General Electric Company System and Method for Airfoil Vibration Control
CA3073417A1 (en) 2019-04-18 2020-10-18 Pratt & Whitney Canada Corp. Fan blade ice protection using hot air
US11118457B2 (en) * 2019-10-21 2021-09-14 Pratt & Whitney Canada Corp. Method for fan blade heating using coanda effect
US11333079B2 (en) * 2020-04-28 2022-05-17 General Electric Company Methods and apparatus to detect air flow separation of an engine
US11828237B2 (en) 2020-04-28 2023-11-28 General Electric Company Methods and apparatus to control air flow separation of an engine
US11085303B1 (en) * 2020-06-16 2021-08-10 General Electric Company Pressurized damping fluid injection for damping turbine blade vibration

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US3572960A (en) * 1969-01-02 1971-03-30 Gen Electric Reduction of sound in gas turbine engines
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FR2370170A1 (fr) * 1976-11-05 1978-06-02 Snecma Procede et dispositif pour la diminution du bruit des turbomachines
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