US3873230A - Stator vane actuating mechanism - Google Patents

Stator vane actuating mechanism Download PDF

Info

Publication number
US3873230A
US3873230A US459836A US45983674A US3873230A US 3873230 A US3873230 A US 3873230A US 459836 A US459836 A US 459836A US 45983674 A US45983674 A US 45983674A US 3873230 A US3873230 A US 3873230A
Authority
US
United States
Prior art keywords
bell
casing
stages
pairs
crank
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.)
Expired - Lifetime
Application number
US459836A
Other languages
English (en)
Inventor
James Reynolds Norris
Frederick Mathew Pendoley
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.)
RTX Corp
Original Assignee
United Aircraft 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
Priority to US459836A priority Critical patent/US3873230A/en
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to CA221,073A priority patent/CA1015277A/en
Priority to DE2512292A priority patent/DE2512292C2/de
Priority to FR7509036A priority patent/FR2267454B1/fr
Publication of US3873230A publication Critical patent/US3873230A/en
Application granted granted Critical
Priority to IT21804/75A priority patent/IT1034694B/it
Priority to IL46975A priority patent/IL46975A/en
Priority to SE7503921A priority patent/SE393838B/xx
Priority to JP50042703A priority patent/JPS581241B2/ja
Priority to GB14601/75A priority patent/GB1493151A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • a further object of the present invention is to reduce the stresses imposed upon an actuation system support structure due to engine case growth and engine case distortion.
  • a vane actuation support structure is isolated, in so far as is possible, from the engine casing.
  • Vane actuation means is connected to bell-crank means and both are entirely supported by this support structure. Pairs of unison rings are connected to and actuated by the bell-crank means in opposite directions whereby the reaction forces transmitted into the support structure are balanced and reduced to a minimum.
  • FIGURE is an external perspective view of a portion of the compressor section of a gas turbine engine showing one embodiment of the invention.
  • the numeral 10 designates the annular casing for the compressor section of an axial flow gas turbine engine. Only a portion of the casing is shown; the forward end of the casing or the inlet end of the engine is to the left in the drawing.
  • the engine includes five stages of adjustable compressor stator vanes, the number not being critical to the invention.
  • the vanes themselves cannot be seen in the drawing but stems of several of the vanes of each stage can be seen extending radially outwardly through openings in the casing 10.
  • the vane stems of the forward most stage are designated by the numeral 12, and the vane stems of the next succeeding stages are designated 14, 16, 18 and 20, respectively.
  • Each of the stages has a unison ring associated therewith.
  • the unison ring of the forward most stage is designated by the numeral 22; and the unison rings of the next succeeding stages are designated 24, 26, 28 and 30, respectively.
  • the unison rings are of the type which is well known in the prior art.
  • the vanes of each stage are connected to their respective unison rings by means of actuating arms 32 in a manner well known to persons having ordinary skill in the art.
  • the unison ring 22 is connected to a bell-crank 34; the unison rings 24, 26 are connected to a bell-crank 36; the unison ring 28 is connected to a bell-crank 38 and the unison ring 30 is connected to a bell-crank 40.
  • the connecting means between the unison rings and the bell-cranks are links 42 secured to brackets 44 which are fixed to the unison rings.
  • the bell-cranks are all pivotally mounted on a support structure generally represented by the numeral 46.
  • the support structure 46 comprises a bell-crank carrier member 48 which is herein shown as being tubular in form and which extends in a direction substantially parallel to the engine axis.
  • the support 46 also includes casing connecting means for securing the bell-crank carrier member to the casing.
  • the casing connecting means includes forward and rearward support members or brackets 50, 52, respectively, which are secured by suitable means such as bolts to flanges on the casing 10 such as for example at 54 and at 56.
  • the forward bracket 50 is flexible in the axial direction to accommodate axial casing growth and deflections so as to reduce stresses imposed on the carrier 48.
  • the carrier 48 is isolated from casing growth and deflection.
  • no more than two spaced apart support members are used to attach the member to the casing.
  • An actuator 58 is also mounted on the bell-crank carrier 48 by suitable means such as the pin and clevis joint at 60.
  • the actuator 58 is connected to the bellcranks 34, 36, 38 and 40 by a connecting rod 62 which may be one piece or several interconnected pieces as shown in this embodiment.
  • the adjustable vane stages are divided into what shall hereinafter be referred to as pairs of balanced stages.
  • the two stages of vanes associated with the unison rings 24 and 26 are an example of one such pair.
  • the unison ring and actuating arms of one stage ofa pair are positioned rearwardly of the vanes of their associated stage, while the unison ring and actuating arms of the other stage of such pair are positioned forwardly of the vanes of their associated stage.
  • the unison ring 24 is positioned rearwardly of the vane stems l4 and the unison ring 26 is positioned forwardly of the vane stems 16.
  • each pair of balanced stages has associated therewith a pair of bell-crank arms such as the arms 64 and 66 of the bell-crank 36.
  • One of the pair of arms extends forwardly of its pivot point, such as the arm 64, and the other of the arms extends rearwardly of its pivot point, such as the arm 66.
  • both arms are part of a single bell-crank 36 and therefore pivot about a common axis 68.
  • Each of the pair of arms 64, 66 is connected to one of the unison rings 24, 26 by means of links 42.
  • FIG. I Another pair of balanced stages is also shown in FIG. I. These are the stages associated with the unison rings 28 and 30. Note once again that the pair of unison rings associated with the pair of balanced stages are positioned on opposite sides of the vanes of their respective stages. The unison ring 28 is positioned forwardly of the vanes of its stage and the unison ring 30 is positioned rearwardly of the vanes of its stage. Note, however, that this pair of balanced stages is actuated through individual bell-cranks 38, 40 rather than a common bell-crank such as the bell-crank 36 which operates two unison rings. As with the previous pair of balanced stages, this pair of balanced stages also has associated therewith a pair of bell-crank arms 70, 72.
  • the bell-crank arm 70 extends rearwardly of its pivot point and the bell-crank 72 extends forwardly of its pivot point.
  • the bell-crank carrier 48 will be subjected to a local bending moment. For that reason a pair of bell-crank arms acting about a common axis, such as the arms 64, 66 is preferred for actuating a pair of balanced stages.
  • space considerations around the engine casing and the spacing between adjustable vane stages will determine whether or not a single or two separate bell-cranks are used to actuate a pair of balanced stages. If it is necessary to use the two separate bell-cranks then it is preferable to have their pivot points as close together as possible to minimize the bending moment generated by the reaction forces.
  • the pairs of balanced stages be adjacent stages such as they are in the exemplary embodiment of FIG. 1.
  • the force required to rotate the vanes in a given stage will likely be different from the force required to rotate the vanes in another stage, and similarly the angle of rotation desired may vary from stage to stage.
  • linkage geometry and the arrangement of pairs of balanced stages are selected such that the summation of reaction forces and moments acting on the bellcrank carrier member 48 is as near zero as possible thus minimizing the loads on brackets 50 and 52 and the engine casing 10.
  • the forwardmost stage is the odd stage.
  • the forward and next to last stages are the pair of balanced stages.
  • a further important feature of the present invention which is in keeping with the purpose of minimizing the loads transmitted to the casing 10 is that the actuator is mounted entirely on the support structure 46 so that the reaction forces associated therewith are confined to the load path loops formed by the support structure 46, the connecting rod 62, the bell-cranks 34, 36, 38, 40 and the actuating cylinder 58. The reaction forces thereby balance each other and are not transmitted into the casing 10.
  • stator vane actuation system comprising:
  • a bell-crank support assembly including substantially a plurality of first actuating arms connected to the a second unison ring for each of said pairs surrounding said casing and disposed forwardly of the vanes of said second stage of each of said pairs, said second actuating arms being connected thereto;
  • said support assembly also including casing connecting means secured to said carrier means and to said casing, and adapted to substantially isolate said carrier means from deflection and axial growth of said casing;
  • bell-crank means including a pair of bell-crank arms for each of said pairs of stages, said arms being pivotally connected to said carrier means, one of said pair of bell-crank arms extending forwardly of its pivot point and the other of said pair of bell-crank arms extending rearwardly of its pivot point, one of said pair of bell-crank arms being connected to said first unison ring and the other of said pair of bellcrank arms being connected to said second unison ring;
  • actuation means mounted entirely on said bell-crank support assembly and connected to said bell-crank means and adapted to simultaneously rotate said pairs of bell-crank arms in the same direction thereby rotating said first and second unison rings of each of said pairs of stages in opposite directions to balance the reaction forces transmitted into said carrier means through each of said pairs of bellcrank arms and to effectuate rotation in the same direction of the vanes of each of said pairs of stages.
  • stator vane actuation system according to claim 1 wherein the stages of each of said pairs of stages are adjacent stages.
  • stator vane actuation system according to claim 1 wherein at least one pair of bell-crank arms is pivotally connected to said carrier means about a common axis.
  • stator vane actuation system according to claim 1 wherein not more than one of said stages of rotatably mounted stator vanes is an unpaired stage.
  • said casing connecting means includes forward support means and rearward support means one of said support means being substantially rigid and the other permitting relative movement between said casing and said carrier means thereby substantially isolating said carrier means from said casing, said forward and rearward support means being the only load paths from said carrier means into said casing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US459836A 1974-04-10 1974-04-10 Stator vane actuating mechanism Expired - Lifetime US3873230A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
US459836A US3873230A (en) 1974-04-10 1974-04-10 Stator vane actuating mechanism
CA221,073A CA1015277A (en) 1974-04-10 1975-02-27 Stator vane actuating mechanism
DE2512292A DE2512292C2 (de) 1974-04-10 1975-03-20 Leitschaufelverstellvorrichtung für einen mehrstufigen Axialverdichter
FR7509036A FR2267454B1 (https=) 1974-04-10 1975-03-24
IT21804/75A IT1034694B (it) 1974-04-10 1975-03-28 Meccanismo per l azionamento delle palette di und statore in un motore a turbina a gas
IL46975A IL46975A (en) 1974-04-10 1975-03-31 Mechanism for operating stator vanes
SE7503921A SE393838B (sv) 1974-04-10 1975-04-07 Manovreringssystem for statorledskovlar
JP50042703A JPS581241B2 (ja) 1974-04-10 1975-04-08 ガスタ−ビン・エンジンのステ−タ−翼作動装置
GB14601/75A GB1493151A (en) 1974-04-10 1975-04-09 Adjustable stator vane assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US459836A US3873230A (en) 1974-04-10 1974-04-10 Stator vane actuating mechanism

Publications (1)

Publication Number Publication Date
US3873230A true US3873230A (en) 1975-03-25

Family

ID=23826320

Family Applications (1)

Application Number Title Priority Date Filing Date
US459836A Expired - Lifetime US3873230A (en) 1974-04-10 1974-04-10 Stator vane actuating mechanism

Country Status (9)

Country Link
US (1) US3873230A (https=)
JP (1) JPS581241B2 (https=)
CA (1) CA1015277A (https=)
DE (1) DE2512292C2 (https=)
FR (1) FR2267454B1 (https=)
GB (1) GB1493151A (https=)
IL (1) IL46975A (https=)
IT (1) IT1034694B (https=)
SE (1) SE393838B (https=)

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4253797A (en) * 1977-09-10 1981-03-03 Motoren-Und Turbinen-Union Munchen Gmbh Apparatus for operating shut-off members in gas turbine engines, particularly in turbojet engines
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system
US4403912A (en) * 1981-03-23 1983-09-13 Avco Corporation Integrated multiplane actuator system for compressor variable vanes and air bleed valve
US4720237A (en) * 1986-02-24 1988-01-19 United Technologies Corporation Unison ring actuator assembly
US4874287A (en) * 1986-02-28 1989-10-17 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Variable-geometry turbocompressor
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
US6457937B1 (en) * 2000-11-08 2002-10-01 General Electric Company Fabricated torque shaft
US6471471B1 (en) * 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US6769868B2 (en) 2002-07-31 2004-08-03 General Electric Company Stator vane actuator in gas turbine engine
US20050129510A1 (en) * 2003-06-20 2005-06-16 Snecma Moteurs Variable pitch device for two blade stages fixed onto a turbojet
US20090226305A1 (en) * 2008-03-07 2009-09-10 Albert Wong Variable vane actuation system
US20110033297A1 (en) * 2008-04-24 2011-02-10 Michael Andre Bouru Device for controlling variable-pitch blades in a turbomachine compressor
US20110085885A1 (en) * 2009-10-09 2011-04-14 Andy Copeland Variable vane actuation system
US20140133968A1 (en) * 2012-11-15 2014-05-15 United Technologies Corporation Bellcrank for a variable vane assembly
US20140205424A1 (en) * 2012-08-29 2014-07-24 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
EP2971599A4 (en) * 2013-03-13 2016-12-21 United Technologies Corp VARIABLE AUB DRIVE SYSTEM
US20180171878A1 (en) * 2016-12-19 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Adjustment device for adjusting several guide vanes of an engine
US10107130B2 (en) 2016-03-24 2018-10-23 United Technologies Corporation Concentric shafts for remote independent variable vane actuation
US10190599B2 (en) 2016-03-24 2019-01-29 United Technologies Corporation Drive shaft for remote variable vane actuation
US10267326B2 (en) 2012-09-27 2019-04-23 United Technologies Corporation Variable vane scheduling
US10288087B2 (en) 2016-03-24 2019-05-14 United Technologies Corporation Off-axis electric actuation for variable vanes
US10294813B2 (en) 2016-03-24 2019-05-21 United Technologies Corporation Geared unison ring for 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
US10329946B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation Sliding gear actuation for variable vanes
US10329947B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation 35Geared unison ring for multi-stage variable vane actuation
US10415596B2 (en) 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes
US10443431B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Idler gear connection for multi-stage variable vane actuation
US10443430B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Variable vane actuation with rotating ring and sliding links
US10458271B2 (en) 2016-03-24 2019-10-29 United Technologies Corporation Cable drive system for variable vane operation
EP3597930A1 (en) * 2018-07-18 2020-01-22 United Technologies Corporation Cam isolation system for gas turbine engine compressor section
DE102022112652A1 (de) 2022-05-19 2023-11-23 MTU Aero Engines AG Vorrichtung zum synchronen Verstellen einer Vielzahl von variablen Verdichterstufen für einen Axialverdichter einer Strömungsmaschine, sowie eine Strömungsmaschine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS605329U (ja) * 1983-06-20 1985-01-16 ヤンマー農機株式会社 コンバイン排藁処理部への排藁供給装置
JP2002159539A (ja) * 2000-11-27 2002-06-04 Toshiba Corp 医用装置の寝台装置
JP2008035927A (ja) * 2006-08-02 2008-02-21 Sophia Precision Corp 鍛練装置
US9103228B2 (en) * 2011-08-08 2015-08-11 General Electric Company Variable stator vane control system
DE102021123772A1 (de) 2021-09-14 2023-03-16 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823700A (en) * 1954-11-19 1958-02-18 Westinghouse Electric Corp Fluid flow control apparatus
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
US3360240A (en) * 1966-01-10 1967-12-26 Rolls Royce Vane operating mechanism
US3487992A (en) * 1967-11-01 1970-01-06 Gen Electric Stator adjusting mechanism for axial flow compressors
US3614253A (en) * 1969-05-29 1971-10-19 Robert M Gaertner Engine stall anticipation and reaction device
US3632224A (en) * 1970-03-02 1972-01-04 Gen Electric Adjustable-blade turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823700A (en) * 1954-11-19 1958-02-18 Westinghouse Electric Corp Fluid flow control apparatus
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
US3360240A (en) * 1966-01-10 1967-12-26 Rolls Royce Vane operating mechanism
US3487992A (en) * 1967-11-01 1970-01-06 Gen Electric Stator adjusting mechanism for axial flow compressors
US3614253A (en) * 1969-05-29 1971-10-19 Robert M Gaertner Engine stall anticipation and reaction device
US3632224A (en) * 1970-03-02 1972-01-04 Gen Electric Adjustable-blade turbine

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4253797A (en) * 1977-09-10 1981-03-03 Motoren-Und Turbinen-Union Munchen Gmbh Apparatus for operating shut-off members in gas turbine engines, particularly in turbojet engines
US4390318A (en) * 1977-09-10 1983-06-28 Mtu Motoren-Und Turbinen-Union Muenche Gmbh Apparatus for operating shut-off members in gas turbine engines, particularly in turbojet engines
US4403912A (en) * 1981-03-23 1983-09-13 Avco Corporation Integrated multiplane actuator system for compressor variable vanes and air bleed valve
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system
US4720237A (en) * 1986-02-24 1988-01-19 United Technologies Corporation Unison ring actuator assembly
US4874287A (en) * 1986-02-28 1989-10-17 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Variable-geometry turbocompressor
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
US6457937B1 (en) * 2000-11-08 2002-10-01 General Electric Company Fabricated torque shaft
US6471471B1 (en) * 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US6769868B2 (en) 2002-07-31 2004-08-03 General Electric Company Stator vane actuator in gas turbine engine
EP1387041A3 (en) * 2002-07-31 2006-05-10 General Electric Company Stator vane actuator in gas turbine engine
US20050129510A1 (en) * 2003-06-20 2005-06-16 Snecma Moteurs Variable pitch device for two blade stages fixed onto a turbojet
US7037070B2 (en) * 2003-06-20 2006-05-02 Snecma Moteurs Variable pitch device for two blade stages fixed onto a turbojet
US20090226305A1 (en) * 2008-03-07 2009-09-10 Albert Wong Variable vane actuation system
US8435000B2 (en) 2008-03-07 2013-05-07 Rolls-Royce Corporation Variable vane actuation system
US20110033297A1 (en) * 2008-04-24 2011-02-10 Michael Andre Bouru Device for controlling variable-pitch blades in a turbomachine compressor
US8784043B2 (en) 2008-04-24 2014-07-22 Snecma Device for controlling variable-pitch blades in a turbomachine compressor
US20110085885A1 (en) * 2009-10-09 2011-04-14 Andy Copeland Variable vane actuation system
US8393857B2 (en) 2009-10-09 2013-03-12 Rolls-Royce Corporation Variable vane actuation system
US20140205424A1 (en) * 2012-08-29 2014-07-24 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US10267326B2 (en) 2012-09-27 2019-04-23 United Technologies Corporation Variable vane scheduling
US9151178B2 (en) * 2012-11-15 2015-10-06 United Technologies Corporation Bellcrank for a variable vane assembly
US20140133968A1 (en) * 2012-11-15 2014-05-15 United Technologies Corporation Bellcrank for a variable vane assembly
EP2971599A4 (en) * 2013-03-13 2016-12-21 United Technologies Corp VARIABLE AUB DRIVE SYSTEM
US10329946B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation Sliding gear actuation for variable vanes
US10443431B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Idler gear connection for multi-stage variable vane actuation
US10107130B2 (en) 2016-03-24 2018-10-23 United Technologies Corporation Concentric shafts for remote independent variable vane actuation
US10288087B2 (en) 2016-03-24 2019-05-14 United Technologies Corporation Off-axis electric actuation for variable vanes
US10294813B2 (en) 2016-03-24 2019-05-21 United Technologies Corporation Geared unison ring for 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
US11131323B2 (en) * 2016-03-24 2021-09-28 Raytheon Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears
US10329947B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation 35Geared unison ring for multi-stage variable vane actuation
US10415596B2 (en) 2016-03-24 2019-09-17 United Technologies Corporation Electric 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
US10458271B2 (en) 2016-03-24 2019-10-29 United Technologies Corporation Cable drive system for variable vane operation
US10578029B2 (en) * 2016-12-19 2020-03-03 Rolls-Royce Deutschland Ltd & Co Kg Adjustment device for adjusting several guide vanes of an engine
US20180171878A1 (en) * 2016-12-19 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Adjustment device for adjusting several guide vanes of an engine
EP3597930A1 (en) * 2018-07-18 2020-01-22 United Technologies Corporation Cam isolation system for gas turbine engine compressor section
US10830086B2 (en) 2018-07-18 2020-11-10 Raytheon Technologies Corporation Cam isolation system for gas turbine engine compressor section
DE102022112652A1 (de) 2022-05-19 2023-11-23 MTU Aero Engines AG Vorrichtung zum synchronen Verstellen einer Vielzahl von variablen Verdichterstufen für einen Axialverdichter einer Strömungsmaschine, sowie eine Strömungsmaschine

Also Published As

Publication number Publication date
FR2267454A1 (https=) 1975-11-07
CA1015277A (en) 1977-08-09
FR2267454B1 (https=) 1981-12-18
JPS581241B2 (ja) 1983-01-10
IL46975A (en) 1977-03-31
JPS50138208A (https=) 1975-11-04
GB1493151A (en) 1977-11-23
DE2512292C2 (de) 1985-01-31
DE2512292A1 (de) 1975-10-23
SE7503921L (sv) 1975-10-13
IL46975A0 (en) 1975-06-25
SE393838B (sv) 1977-05-23
IT1034694B (it) 1979-10-10

Similar Documents

Publication Publication Date Title
US3873230A (en) Stator vane actuating mechanism
US4430043A (en) Variable stator vane operating mechanism for turbomachines
US4295784A (en) Variable stator
US4720237A (en) Unison ring actuator assembly
US4755104A (en) Stator vane linkage
US4961310A (en) Single shaft combined cycle turbine
US3458118A (en) Low profile stator adjusting mechanism
US4785625A (en) Ducted fan gas turbine power plant mounting
US2933234A (en) Compressor stator assembly
US5443229A (en) Aircraft gas turbine engine sideways mount
US4502276A (en) Casing structure for a gas turbine engine
US8444084B2 (en) Aeroengine mounting
US11542022B2 (en) Aircraft propulsion assembly
GB1368353A (en) Actuation ring for variable geometry axial flow compressors
US3869221A (en) Rotor wheel fan blade adjusting apparatus for turbojet engines and the like
GB2238354A (en) Blade tip clearance control apparatus
US4373859A (en) Unison ring support system
US4400135A (en) Vane actuation system
SE453768B (sv) Munstycksaggregat med varierbar area for gasturbinmotorer
US11851201B2 (en) Turbomachine comprising a means of suspension
GB1216920A (en) Axial flow compressors having adjustable stator vanes
EP3095969B1 (en) Casing assembly
US2917275A (en) Turbo machines having adjustable guide blades
JPH10103154A (ja) 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル
US4310286A (en) Rotor assembly having a multistage disk