US20120141248A1 - Active fan flutter control - Google Patents

Active fan flutter control Download PDF

Info

Publication number
US20120141248A1
US20120141248A1 US12/959,802 US95980210A US2012141248A1 US 20120141248 A1 US20120141248 A1 US 20120141248A1 US 95980210 A US95980210 A US 95980210A US 2012141248 A1 US2012141248 A1 US 2012141248A1
Authority
US
United States
Prior art keywords
fan
fan case
controller
flutter
turbomachine
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.)
Abandoned
Application number
US12/959,802
Other languages
English (en)
Inventor
William E. Rhoden
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Priority to US12/959,802 priority Critical patent/US20120141248A1/en
Priority to EP11191831.4A priority patent/EP2461010B1/fr
Publication of US20120141248A1 publication Critical patent/US20120141248A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/15—Control or regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes

Definitions

  • the subject matter disclosed herein relate to turbine engines. More specifically, the subject disclosure relates to control of flutter of fan blades of turbine engines.
  • Turbine engines include a fan section having a number of airfoils, or fan blades, extending from a hub. In large turbine engines these fan blades can exceed five feet in length. The length and ratio of length to chord of fan blades leaves them susceptible to flow induced vibration, also known as flutter. Fan blade flutter can lead to structural damage to and failure of the fan blade, and liberation of the fan blade from the hub which results damage to components and potentially failure of the turbine engine. Fan blades typically are susceptible to flutter during certain operation conditions of the turbine engine. Typically, flutter is avoided by avoiding those operating conditions which may lead to flutter. This, however, places undesirable restrictions on the operation of the turbine engine.
  • a flutter control system for a turbomachine fan includes a plurality of fan case sensors located at a fan case of the turbomachine and configured to sense passing of blade tips of a fan of the turbomachine.
  • a controller is operably connected to the plurality of fan case sensors.
  • a variable fan area nozzle actuator is operably connected to the controller, such that the variable fan area nozzle actuator urges a change in fan nozzle area in response to data from the plurality of fan case sensors indicating flutter or near flutter conditions.
  • a method of flutter control for a turbomachine fan includes sensing a blade tip passing of a plurality of fan blades via a plurality of fan case sensors disposed at a fan case of a turbomachine. Data from the plurality of fan case sensors is compared to a threshold and a fan exit area is changed based on the comparison to dampen flutter of the plurality of fan blades.
  • FIG. 1 is a schematic of an exemplary embodiment of an active flutter control system
  • FIG. 2 is a schematic of another exemplary embodiment of an active flutter control system.
  • FIG. 1 Shown in FIG. 1 is a schematic of an embodiment of an active flutter control system 10 .
  • the system includes a plurality of tip timing probes 12 located in a fan case 14 of a turbomachine 16 .
  • the tip timing probes 12 are located to observe arrival timing of a plurality of fan blades 18 fixed to a fan shaft 20 as the plurality of fan blades 18 rotate about a fan axis 22 .
  • three tip timing probes 12 are utilized, located in the fan case 14 substantially to monitor passing of a leading edge 24 , trailing edge 26 , and mid-chord 28 of the plurality of fan blades 18 .
  • the tip timing probes 12 monitoring the leading edge 24 and trailing edge 26 are utilized to determine fan blade 18 twist.
  • the tip timing probes 12 at mid-chord 28 monitor tip timing to determine flex of the fan blades 18 . Even though three tip timing probes 12 are utilized in the embodiment of FIG. 1 , it is to be appreciated that other quantities of tip timing probes 12 , for example, five or six tip timing probes 12 , may be used. Further, groups of tip timing probes 12 may be positioned radially around the fan case 14 , for example at 12 o'clock, 4 o'clock, and 8 o'clock positions. This allows for collection of more tip passing data and correlation and/or verification of data when taken at multiple locations around the fan case 14 .
  • the information from the tip timing probes 12 is communicated to a full authority digital engine control (FADEC) 30 .
  • the FADEC 30 compares the passing timing of the fan blades 18 to a threshold, to determine if a fan blade 18 is approaching a flutter condition or is actively fluttering. Based on the comparison, the FADEC 30 sends commands to a variable fan area nozzle (VFAN) actuator 32 .
  • VFAN variable fan area nozzle
  • the VFAN actuator 32 drives a VFAN 34 to change a fan exit area 36 .
  • the change to fan exit area 36 ensures that sufficient back pressure is applied to the fan blades 18 to dampen out flutter as measured by the tip timing probes 12 .
  • FIG. 2 Another embodiment of a flutter control system 10 is shown in FIG. 2 .
  • a plurality of radio frequency (RF) probes 38 located in the fan case 14 to observe arrival timing of the plurality of fan blades 18 .
  • three RF probes 38 are utilized, located in the fan case 14 substantially to monitor passing of the leading edge 24 , trailing edge 26 , and mid-chord 28 of the plurality of fan blades 18 .
  • the RF probes 38 monitoring the leading edge 24 and trailing edge 26 are utilized to determine fan blade 18 twist.
  • the tip timing probes 12 at mid-chord 28 monitor tip timing to determine flex of the fan blades 18 .
  • a plurality of strain gauges 40 are arranged along a span 42 of the fan blade 18 and are connected to a radio frequency identification (RFID) tag 44 at the fan blade 18 .
  • RFID radio frequency identification
  • the strain gauges 40 are arranged substantially linearly along the span 42 , but this arrangement is merely exemplary. Any appropriate arrangement of strain gauges 40 , for example, placement of strain gauges 40 at known high stress points, is contemplated within the present scope.
  • the RFID tag 44 communicates with one or more of the RF probes 38 to relay data from the plurality of strain gauges 40 to the FADEC 30 .
  • the FADEC 30 utilizes data from the plurality of strain gauges 40 and the RF probes 38 to determine flutter status of the fan blades 18 .
  • Utilizing the plurality of strain gauges 40 and the RFID tag 44 provides the FADEC 30 with more data to more accurately determine the flutter status of the plurality of fan blades 18 .
  • the FADEC 30 is linked to the VFAN actuator 32 to change the fan exit area 36 to mitigate flutter of the plurality of fan blades 18 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/959,802 2010-12-03 2010-12-03 Active fan flutter control Abandoned US20120141248A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US12/959,802 US20120141248A1 (en) 2010-12-03 2010-12-03 Active fan flutter control
EP11191831.4A EP2461010B1 (fr) 2010-12-03 2011-12-02 Systeme et procédé de contrôle actif des tremblements de soufflante

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/959,802 US20120141248A1 (en) 2010-12-03 2010-12-03 Active fan flutter control

Publications (1)

Publication Number Publication Date
US20120141248A1 true US20120141248A1 (en) 2012-06-07

Family

ID=45346276

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/959,802 Abandoned US20120141248A1 (en) 2010-12-03 2010-12-03 Active fan flutter control

Country Status (2)

Country Link
US (1) US20120141248A1 (fr)
EP (1) EP2461010B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130111915A1 (en) * 2011-11-04 2013-05-09 Frederick M. Schwarz System for optimizing power usage from damaged fan blades
US20140321988A1 (en) * 2013-04-29 2014-10-30 Dresser Inc. Device for modifying flow parameters of working fluid exiting a compressor device

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3387263B1 (fr) * 2015-12-11 2021-04-07 General Electric Company Système de surveillance et de commande de flottement d'aube de turbine à gaz
US11305894B2 (en) * 2018-11-30 2022-04-19 Gulfstream Aerospace Corporation Detection of fan case liner damage during turbine engine operation
FR3097898B1 (fr) * 2019-06-26 2021-06-25 Safran Aircraft Engines Dechargement d’une veine d’un ensemble propulsif pour reduire le battement des aubes d’une soufflante

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5141391A (en) * 1986-04-28 1992-08-25 Rolls-Royce, Plc Active control of unsteady motion phenomena in turbomachinery
US6582183B2 (en) * 2000-06-30 2003-06-24 United Technologies Corporation Method and system of flutter control for rotary compression systems
US20070043497A1 (en) * 2005-08-16 2007-02-22 United Technologies Corporation Systems and methods for monitoring thermal growth and controlling clearances, and maintaining health of turbo machinery applications
US20080273961A1 (en) * 2007-03-05 2008-11-06 Rosenkrans William E Flutter sensing and control system for a gas turbine engine
US7824147B2 (en) * 2006-05-16 2010-11-02 United Technologies Corporation Airfoil prognosis for turbine engines

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US8111161B2 (en) * 2009-02-27 2012-02-07 General Electric Company Methods, systems and/or apparatus relating to turbine blade monitoring

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5141391A (en) * 1986-04-28 1992-08-25 Rolls-Royce, Plc Active control of unsteady motion phenomena in turbomachinery
US6582183B2 (en) * 2000-06-30 2003-06-24 United Technologies Corporation Method and system of flutter control for rotary compression systems
US20070043497A1 (en) * 2005-08-16 2007-02-22 United Technologies Corporation Systems and methods for monitoring thermal growth and controlling clearances, and maintaining health of turbo machinery applications
US7824147B2 (en) * 2006-05-16 2010-11-02 United Technologies Corporation Airfoil prognosis for turbine engines
US20080273961A1 (en) * 2007-03-05 2008-11-06 Rosenkrans William E Flutter sensing and control system for a gas turbine engine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130111915A1 (en) * 2011-11-04 2013-05-09 Frederick M. Schwarz System for optimizing power usage from damaged fan blades
US9051897B2 (en) * 2011-11-04 2015-06-09 United Technologies Corporation System for optimizing power usage from damaged fan blades
US20140321988A1 (en) * 2013-04-29 2014-10-30 Dresser Inc. Device for modifying flow parameters of working fluid exiting a compressor device

Also Published As

Publication number Publication date
EP2461010B1 (fr) 2015-09-23
EP2461010A1 (fr) 2012-06-06

Similar Documents

Publication Publication Date Title
EP1857637B1 (fr) Procédé de prédiction de la durée de vie utile restante d'une aube d'une turbine à gaz
EP2461010B1 (fr) Systeme et procédé de contrôle actif des tremblements de soufflante
JP5227314B2 (ja) 空気力学的表面での氷結の危険性を検出するシステム
EP3034812B1 (fr) Surveillance d'un capteur de couple pour moteur de turbine à gaz
US7927067B2 (en) System and method for controlling stator assemblies
US10908050B2 (en) Methods and systems for monitoring rotor blades in turbine engines
EP2273168B1 (fr) Détection des fautes des vannes
CN103592053A (zh) 用于涡轮发动机的蠕变寿命管理系统及操作其的方法
US20140007591A1 (en) Advanced tip-timing measurement blade mode identification
EP3055210B1 (fr) Procédé pour diagnostiquer une panne d'unité d'alimentation auxiliaire
EP3064779B1 (fr) Moteur à turbine à gaz avec système d'amortissement à profil aérodynamique
CN102331341B (zh) 用于监测翼型件的健康状况的系统和方法
TWI547639B (zh) Determination of Abnormal Degree of Wind Turbine Generator and Judgment of Abnormal Degree of Wind Turbine
US11193388B2 (en) Methods and systems for monitoring rotor blades in turbine engines
US10908049B2 (en) Methods and systems for monitoring rotor blades in turbine engines
EP1980719A2 (fr) Turbomachine avec capteur à micro-ondes
US10132189B2 (en) Variable vane control system
JP2008537768A (ja) ブレード先端部のクリアランス制御システム
EP2522818A2 (fr) Mesure de température radiale d'entretoise d'échappement
EP2586998A2 (fr) Capteurs de mesure disposés radialement dans une turbine
CN111720218B (zh) 涡轮发动机的信号响应监测
US9897431B2 (en) Edge detector
US20150000247A1 (en) System and method for detecting airfoil clash within a compressor
US9404386B2 (en) System and method for monitoring health of airfoils
CN114746625A (zh) 用于识别裂纹的涡轮叶片健康监测系统

Legal Events

Date Code Title Description
STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION