EP1724472A2 - Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine - Google Patents

Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine Download PDF

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Publication number
EP1724472A2
EP1724472A2 EP06112991A EP06112991A EP1724472A2 EP 1724472 A2 EP1724472 A2 EP 1724472A2 EP 06112991 A EP06112991 A EP 06112991A EP 06112991 A EP06112991 A EP 06112991A EP 1724472 A2 EP1724472 A2 EP 1724472A2
Authority
EP
European Patent Office
Prior art keywords
ring
follower
control system
arm
housing
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
EP06112991A
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English (en)
French (fr)
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EP1724472A3 (de
EP1724472B1 (de
Inventor
Michel Bouru
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1724472A2 publication Critical patent/EP1724472A2/de
Publication of EP1724472A3 publication Critical patent/EP1724472A3/de
Application granted granted Critical
Publication of EP1724472B1 publication Critical patent/EP1724472B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams

Definitions

  • the present invention relates to the general field of the blade stage control variable pitch angle of a turbomachine.
  • stator vane stages each include a plurality of vanes (referred to as variable pitch vanes) that are pivotable about their stator connection axis so that their stall angle can be varied according to the operating regime. of the turbomachine.
  • Known devices for controlling a stage of variable pitch vanes usually comprise a control member in the form of a ring surrounding the casing of the turbomachine and a plurality of rods or levers, each rod having a first end connected to the control ring by a hinge and a second end mounted on the pivot of a respective blade.
  • An actuating jack is connected to the control ring in order to rotate the latter around the axis of the turbomachine. The rotation of the ring around the axis of the turbomachine causes a synchronized modification of the angular position of the blades of the stage.
  • This control system generates movements on the various ordered stages represented in the form of curves which show the angle of wedging of the vanes of the follower stage as a function of the wedging angle of the vanes of the pilot stage.
  • these curves called correlation curves, have a progressive slope evolution. Also, this type of control system allows only simple commands of the blade stages.
  • each rod of the pilot stage is connected to the corresponding control ring by a groove connection and pin sliding in the groove.
  • This control system is however not fully satisfactory because it does not allow in particular to reproduce a correlation curve having a sudden acceleration or deceleration of the slope.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing a control system which makes it possible to produce a law for setting the blades having an acceleration (or deceleration) on a localized zone of the control trajectory.
  • a control system of two stator vane stages with a variable turbine engine pitch angle each stage being formed of a plurality of vanes which are each mounted pivotally on a casing of the turbine engine.
  • the control system comprising an actuating element for rotating the control ring of the one stages by means of a pilot member pivotally mounted on the housing, and a synchronization bar for transmitting the rotational movement of the ring driven by the operating element to the control ring of the other floor by via a follower member pivotally mounted on the housing, characterized in that it further comprises an additional pivoting member interposed between the follower member and the follower ring, said additional pivoting member being pivotally mounted both on the housing and on the follower.
  • follower ring is meant the control ring which is rotated through the follower member.
  • the additional pivoting member comprises an arm pivotally mounted on a control rod connected to the follower ring and a sliding guide rod in a ring pivotally mounted on the casing.
  • the follower member comprises a first arm pivotally connected to the additional pivoting member and a second arm connected to one end of the synchronization bar.
  • the point of pivoting on the casing of the additional pivoting member may be arranged inside a circle having as a center the point of pivoting on the housing of the follower member and for radius the first arm of the follower member. . In this case, it is then an acceleration of the control path.
  • the point of pivoting on the casing of the additional pivoting member may be arranged outside a circle having the center of the pivot point on the housing of the follower member and for radius the first arm of the follower organ. In this case, it is then a deceleration of the control path.
  • the pilot member comprises a first arm connected to the ring of the pilot stage via a second control rod, a second arm connected to the end of the synchronization bar opposite to that connected to the follower member and a third arm connected to the operating element.
  • FIG. 1 partially shows two stages 10, 10 'of variable pitch vanes belonging, for example, to a turbomachine compressor.
  • the compressor comprises an annular stator envelope 12 (or casing) which is centered on the X-X axis of the turbomachine.
  • the stages 10, 10 'of blades are offset axially relative to each other.
  • Each stage consists of a plurality of vanes 14, 14 'arranged radially around the X-X axis of the turbomachine.
  • the blades 14, 14 ' are pivotable about an axis 16, 16' (or pivot) which passes through the housing 12.
  • Each pivot 16, 16 'of the variable pitch vanes 14, 14' is connected to one end of a rod or control lever 18, 18 'whose other end is articulated around pins 20, 20' arranged radially on a control ring 22, 22 '.
  • the control rings surround the casing 12 and are centered on the X-X axis of the turbomachine.
  • the synchronized modification of the angular position of the blades 14, 14 ' is thus achieved by rotation of the respective control rings 22, 22' around the axis X-X of the turbomachine.
  • the system according to the invention makes it possible to synchronously control the rotation of the control rings 22, 22 'around the axis XX of the turbomachine. It comprises a actuating element 24 of the jack type fixed to the casing 12 in order to drive in rotation the ring of control 22 of one of the stages 10 by means of a pilot member 26 of return type which is pivotally mounted on a housing 28 of the housing 12 of the turbomachine.
  • a synchronization bar 30 makes it possible to transmit the rotational movement of the ring 22 driven by the jack 24 (called the pilot ring) to the ring 22 'of the other stage 10' (called the follower ring) via a follower member 26 'which is also pivotally mounted on the housing 28 of the housing 12.
  • Control rods 32, 32 'of screw-type turnbuckles provide transmission of the movement of the pilot 26 and follower 26' to the rings 22, 22 '. These rods extend tangentially to the rings on which they are fixed by means of connecting yokes 27, 27 '. At their opposite end, the connecting rods 32, 32 'are attached to respective arms (or branches) 34, 36 of the pilot 26 and follower 26' references hinged thereto.
  • the synchronization bar 30 of the control system unites two other respective arms 38, 40 of the pilot 26 and follower 26 'references hinged thereto. As for the jack 24, it is articulated to a third arm 42 of the pilot gear 26 opposite the arm 34 on which is fixed the connecting rod 32.
  • the control system according to the invention further comprises an additional pivoting member 44 (or additional reference) which is interposed between the follower member 26 'and the follower ring 22'.
  • This additional reference is pivotally mounted on both the housing 12 and the follower member 26 '.
  • the additional return 44 comprises a first arm 46, one end of which is connected to the control rod 32 'of the follower ring 22' by being hinged to it and the other end is pivotally mounted on the follower 26 .
  • the additional return also includes a second arm 48 extending perpendicularly to the first arm 46 along the axis of pivoting of the additional return on the follower.
  • a guide rod 50 is attached to one end of the second arm 48.
  • the guide rod 50 of the additional return wheel 44 is able to slide in a ring 52 pivotally mounted on the casing 12.
  • the sliding ring 52 is for example a recirculation ring of rolling elements. It is pivotally attached to the housing 12, for example by means of a pivoting support 54 brazed to the housing.
  • the movement of the control system is as follows: the actuation of the jack 24 causes a rotation of the pilot return 26, and another of the follower 24 'via the synchronization bar 30.
  • the rotation of the references 26, 26 'around their point of pivoting on the housing 12 in turn drives the respective rods 32, 32' which then rotate in one direction or the other the rings 22, 22 'around of the axis XX of the turbomachine.
  • the rotation of the rings causes a synchronized change in the angular position of the blades 14, 14 'of each stage 10, 10' by means of the control levers 18, 18 '.
  • FIG. 2C represents more precisely the movement of the additional return 44.
  • this figure only shows the follower 26 'and the additional return 44 in two extreme positions of the control system of FIG. dotted, the system in the position in opening of wedging and in solid lines, the system in the position in closure of rigging.
  • the guide rod 50 From a certain position of the pivot point 44a of the additional return 44, hereinafter referred to as the tilting position, the guide rod 50 will cause, by leverage, an accelerated rotation of the first arm 46 of the additional return wheel 44 around its pivot point 44a in the direction of rotation of the follower 26 '. This accelerated rotation of the first arm of the additional reference thereby, via the rod, an acceleration of the rotation of the follower ring in wedging closure.
  • the angle e schematized in FIG. 2C represents the angular acceleration experienced by the additional return 44 with respect to a control system without such a device.
  • the tilting position of the pivot point 44a of the additional return 44 can be defined as the position from which more than half the length of the guide rod 50 has slid into the ring 52. Also, this tilting position can be adjusted by changing the position of the pivoting support 54 of the ring 52 and / or the length of the guide rod to choose the area of the control path to be accelerated. This zone can be as well at the beginning, middle or at the end of the trajectory.
  • FIG. 3 illustrates the effect on the law of wedging of the blades of such an acceleration.
  • Dotted line is represented a correlation curve 100 (that is to say the curve giving the angle of wedging of the vanes of the follower stage as a function of the wedging angle of the vanes of the pilot stage) for a control system without additional return and in solid lines is shown schematically the correlation curve 102 established for the control system according to the invention.
  • the correlation curve 100 established for a control system devoid of additional reference is gradual slope.
  • the correlation curve 102 has a clear acceleration of the angle of wedging of the blades of the follower stage in an angular zone 104.
  • the acceleration zone 104 is at the end of its trajectory, that is to say, in locking closure. As previously explained, it could be localized differently.
  • the pivoting support 54 of the ring 52 (which corresponds to the pivot point on the housing of the additional reference 44) is arranged inside a circle C having for center of the pivot point 26'a on the casing of the follower member 26 'and for radius the arm 36 of the follower member on which is mounted the additional return 44.
  • Such a configuration has the consequence of accelerating the control path.
  • a deceleration is indeed obtained by arranging the pivoting support 54 of the ring 52 outside the circle C as defined above.
  • the pivoting support 54 of the ring 52 outside the circle C and / or the length of the guide rod 50, it is also possible to choose the zone of the control path which must be decelerated (beginning, middle or end).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP06112991A 2005-05-17 2006-04-24 Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine Active EP1724472B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0504918A FR2885969B1 (fr) 2005-05-17 2005-05-17 Systeme de commande d'etages d'aubes de stator a angle de calage variable de turbomachine

Publications (3)

Publication Number Publication Date
EP1724472A2 true EP1724472A2 (de) 2006-11-22
EP1724472A3 EP1724472A3 (de) 2009-01-21
EP1724472B1 EP1724472B1 (de) 2010-06-16

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EP06112991A Active EP1724472B1 (de) 2005-05-17 2006-04-24 Kontrollanlage für verstellbare Leitschaufelstufen einer Turbomaschine

Country Status (7)

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US (1) US7322790B2 (de)
EP (1) EP1724472B1 (de)
JP (1) JP4773876B2 (de)
CA (1) CA2547026C (de)
DE (1) DE602006014902D1 (de)
FR (1) FR2885969B1 (de)
RU (1) RU2396438C2 (de)

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FR2936565A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine notamment, par guignols articules.
FR2936556A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols.
FR2936559A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine faisant partie de corps differents.
CN101311554B (zh) * 2007-05-24 2010-05-26 中国科学院工程热物理研究所 叶片式流体机械的导叶、静叶、转速可调三因素匹配方法
WO2010149725A1 (fr) 2009-06-26 2010-12-29 Snecma Procede et dispositif de recalage de la commande d'un equipement a geometrie variable pour turbomachine
WO2010149724A1 (fr) 2009-06-26 2010-12-29 Snecma Dispositif et methode de positionnement d'un equipement a geometrie variable pour une turbomachine, utilisant un verin a mesure relative
CN102758654A (zh) * 2011-04-21 2012-10-31 通用电气公司 独立控制的燃气涡轮进口导叶和变距定子叶片
WO2014016512A1 (fr) * 2012-07-27 2014-01-30 Aircelle Dispositif d'entrainement de volets notamment pour tuyère adaptative
EP2703606A1 (de) * 2012-08-29 2014-03-05 General Electric Company System und Verfahren zur Steuerung verstellbarer Leitschaufeln in Gasturbinenmotoren
EP2258926A3 (de) * 2009-05-01 2015-01-14 Rolls-Royce plc Steuerungsmechanismus
FR3076325A1 (fr) * 2017-12-29 2019-07-05 Safran Aircraft Engines Dispositif de calage variable d'au moins deux rangees annulaires d'aubes fixes pour une turbomachine
EP3770381A1 (de) * 2019-07-25 2021-01-27 Raytheon Technologies Corporation Selbsthaltendes gestänge und system mit dem selbsthaltenden gestänge für einen gasturbinenmotor

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FR2936558B1 (fr) * 2008-09-30 2016-11-11 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
JP5398323B2 (ja) * 2009-03-30 2014-01-29 三菱重工業株式会社 静翼可変装置および軸流式流体機械
FR2950927B1 (fr) * 2009-10-06 2016-01-29 Snecma Systeme de commande de la position angulaire d'aubes de stator et procede d'optimisation de ladite position angulaire
IT1400053B1 (it) * 2010-05-24 2013-05-17 Nuovo Pignone Spa Metodi e sistemi per ugelli di ingresso a geometria variabile per uso in turboespansori.
IT1401665B1 (it) * 2010-08-31 2013-08-02 Nuova Pignone S R L Sistema di azionamento per turbomacchina e metodo.
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JP5340333B2 (ja) * 2011-03-07 2013-11-13 株式会社日立製作所 軸流圧縮機の改造方法
RU2474698C1 (ru) * 2011-10-28 2013-02-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Система управления ступенями поворотных лопаток статора компрессора высокого давления
DE102012007129A1 (de) * 2012-04-10 2013-10-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
US9885291B2 (en) * 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9879561B2 (en) * 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US20140205424A1 (en) * 2012-08-29 2014-07-24 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
DE102012021876A1 (de) 2012-11-07 2014-05-22 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
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WO2014205816A1 (en) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Guide vane actuator of a compressor and a compressor using it
EP3090142B1 (de) * 2013-12-11 2019-04-03 United Technologies Corporation Verstellbare leitschaufelpositionierungsvorrichtung für einen gasturbinenmotor
FR3025577B1 (fr) * 2014-09-05 2016-12-23 Snecma Mecanisme d'entrainement d'organes de reglage de l'orientation des pales
CN105570196B (zh) * 2014-10-31 2019-09-06 特灵国际有限公司 致动进口导叶的连杆机构
FR3033007B1 (fr) * 2015-02-19 2018-07-13 Safran Aircraft Engines Dispositif pour le reglage individuel d'une pluralite d'aubes radiales fixes a calage variable dans une turbomachine
US10443431B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Idler gear connection for multi-stage variable vane actuation
US10301962B2 (en) 2016-03-24 2019-05-28 United Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears
US10294813B2 (en) 2016-03-24 2019-05-21 United Technologies Corporation Geared unison ring for variable vane actuation
US10288087B2 (en) 2016-03-24 2019-05-14 United Technologies Corporation Off-axis electric actuation for variable vanes
US10458271B2 (en) 2016-03-24 2019-10-29 United Technologies Corporation Cable drive system for variable vane operation
US10107130B2 (en) 2016-03-24 2018-10-23 United Technologies Corporation Concentric shafts for remote independent variable vane actuation
US10415596B2 (en) 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes
US10329946B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation Sliding gear actuation for variable vanes
US10190599B2 (en) 2016-03-24 2019-01-29 United Technologies Corporation Drive shaft for remote variable vane actuation
US10443430B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Variable vane actuation with rotating ring and sliding links
US10329947B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation 35Geared unison ring for multi-stage variable vane actuation
FR3051826B1 (fr) * 2016-05-25 2018-06-01 Safran Aircraft Engines Dispositif de commande d'elements a calage variable dans une turbomachine
US11092167B2 (en) * 2018-08-28 2021-08-17 Pratt & Whitney Canada Corp. Variable vane actuating system
US11092032B2 (en) * 2018-08-28 2021-08-17 Pratt & Whitney Canada Corp. Variable vane actuating system
FR3107319B1 (fr) * 2020-02-19 2022-08-12 Safran Aircraft Engines Module de turbomachine equipe de systeme de changement de pas des pales d’aubes de stator
US11371380B2 (en) * 2020-12-01 2022-06-28 Pratt & Whitney Canada Corp. Variable guide vane assembly and vane arms therefor
PL437817A1 (pl) * 2021-05-07 2022-11-14 General Electric Company Układ o zmiennej geometrii i działaniu rozdzielonym do sprężarki silnika turbinowego
FR3123323B1 (fr) * 2021-05-27 2024-05-03 Safran Aircraft Engines Structure de liaison et de support d’une turbomachine a un pylone d’aeronef
US11802490B2 (en) * 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
US11788429B2 (en) * 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
DE102022103922A1 (de) * 2022-02-18 2023-08-24 MTU Aero Engines AG Hebel zum verstellen einer verstellschaufel

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US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
EP0765992A1 (de) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Betätigungseinrichtung für verstellbare Statorschaufeln
EP0909880A2 (de) * 1997-10-14 1999-04-21 General Electric Company Leitschaufel Verstellsystem für Turbinen
EP1489267A1 (de) * 2003-06-20 2004-12-22 Snecma Moteurs Verstelleinrichtung für zwei Leitschaufelstufen einer Turbomaschine

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US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
EP0765992A1 (de) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Betätigungseinrichtung für verstellbare Statorschaufeln
EP0909880A2 (de) * 1997-10-14 1999-04-21 General Electric Company Leitschaufel Verstellsystem für Turbinen
EP1489267A1 (de) * 2003-06-20 2004-12-22 Snecma Moteurs Verstelleinrichtung für zwei Leitschaufelstufen einer Turbomaschine

Cited By (24)

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US8328500B2 (en) 2008-09-30 2012-12-11 Snecma System for controlling variable-geometry equipments of a turbomachine, particularly by articulated bellcranks
US8591173B2 (en) 2008-09-30 2013-11-26 Snecma System for controlling variable geometry apparatuses in a turbine engine
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WO2010037749A1 (fr) * 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols
US8690521B2 (en) 2008-09-30 2014-04-08 Snecma System for controlling variable geometry equipment for a turbine engine, especially by bellcranks
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FR2993932A1 (fr) * 2012-07-27 2014-01-31 Aircelle Sa Dispositif d'entrainement de volets notamment pour tuyere adaptative
WO2014016512A1 (fr) * 2012-07-27 2014-01-30 Aircelle Dispositif d'entrainement de volets notamment pour tuyère adaptative
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FR3076325A1 (fr) * 2017-12-29 2019-07-05 Safran Aircraft Engines Dispositif de calage variable d'au moins deux rangees annulaires d'aubes fixes pour une turbomachine
US11149580B2 (en) 2019-07-25 2021-10-19 Raytheon Technologies Corporation Self retained linkage and system including the self retained linkage for a gas turbine engine
EP3770381A1 (de) * 2019-07-25 2021-01-27 Raytheon Technologies Corporation Selbsthaltendes gestänge und system mit dem selbsthaltenden gestänge für einen gasturbinenmotor

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CA2547026C (fr) 2013-09-17
EP1724472A3 (de) 2009-01-21
RU2396438C2 (ru) 2010-08-10
FR2885969B1 (fr) 2007-08-10
JP2006322457A (ja) 2006-11-30
US20060263206A1 (en) 2006-11-23
US7322790B2 (en) 2008-01-29
FR2885969A1 (fr) 2006-11-24
CA2547026A1 (fr) 2006-11-17
JP4773876B2 (ja) 2011-09-14
EP1724472B1 (de) 2010-06-16
RU2006116817A (ru) 2007-11-27
DE602006014902D1 (de) 2010-07-29

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