US3314595A - Adjustment mechanism for axial flow compressors - Google Patents

Adjustment mechanism for axial flow compressors Download PDF

Info

Publication number
US3314595A
US3314595A US462688A US46268865A US3314595A US 3314595 A US3314595 A US 3314595A US 462688 A US462688 A US 462688A US 46268865 A US46268865 A US 46268865A US 3314595 A US3314595 A US 3314595A
Authority
US
United States
Prior art keywords
segments
control lever
stator
inserts
intermediate member
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
US462688A
Other languages
English (en)
Inventor
Joseph C Burge
Richard W Follmer
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US462688A priority Critical patent/US3314595A/en
Priority to FR85071A priority patent/FR1501627A/fr
Priority to BE691934D priority patent/BE691934A/xx
Application granted granted Critical
Publication of US3314595A publication Critical patent/US3314595A/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
    • 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
    • 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
    • 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

  • the present invention relates to improvements in axial flow compressors of the type advantageously used in gas turbine engines and more particularly to improved adjustment mechanism therefor.
  • Compressors of the so caller variable geometry or adjustable stator type have been found highly effective for pressurizing air to support combustion in gas turbine engines particularly where such engines are used for the propulsion of aircraft.
  • Compressors of the type referred to comprise a casing and a rotor having stator and rotor blades mounted respectively thereon.
  • the stator and rotor blades are disposed in alternate circumferential rows, with each adjacent pair of rows forming a compressor stage.
  • the blades are disposed generally radially of the rotor with the stator blades of at least the initial stages being pivotal about these radial axes.
  • the objects of the invention are to provide simple and economical mechanism for adjusting stators in axial flow compressors as well as to provide such adjusting mechanism which fulfills the high performance requirements of axial flow compressors employed in gas turbine engines used for the propulsion of aircraft, these high performance requirements including accuracy, lightness of weight and the ability to respond to control signals generated by computer mechanism which determines the desired angular relationships of the stators.
  • levers are secured to each of the stators of an axial flow compressor of the type above described.
  • these levers are relatively thin and plate-like and extend in a plane normal to the axes of the stators to which they are attached.
  • An actuator ring is provided for each row of adjustable stators and these levers are pivotally connected thereto. 1
  • the actuator rings encompass the compressor casing and each comprises a pair of arcuate segments and connectors overlapping the segments and secured thereto to compositely form a ring.
  • the segments and connectors are advantageously tubular in all or certain portions.
  • the pivotal connections are advantageously made by providing openings in the outer walls of the segments and like openings in the inner walls of the connectors. Tubular inserts project through these openings into circumferential slots in the opposite wall.
  • the stator levers then have pins which project into these tubular inserts, the pins projecting inwardly or outwardly depending on whether they are received by the inserts in the segments or inserts in the connectors.
  • these inserts are formed of polytetrafluoroethylene impregnated with glass fibers. This gives necessary strength while providing a minimum of friction in the pivotal connection.
  • Selected, spaced inserts on the segments have thrust buttons secured to their inner ends which engage bearing 3,314,595 Patented Apr. 18, 1967 ICC pads on the compressor casing to more accurately position the actuator rings concentrically of the casing.
  • a control lever having an I-shaped cross section is pivotally mounted at one end on the compressor casing with its opposite end guided for movement in a flat plane.
  • An actuator which is responsive to engine control signals, is connected to the movable end of the control lever.
  • Each of the actuator rings is then connected to the control lever by a light weight, adjustable link so that movement of the control lever will be transmitted to the actuator rings and cause the desired simultaneous adjustment of the stators.
  • the adjustable links each comprise a clevis connected to the control lever, tubular intermediate member rotatable in a hole in the bridge of the clevis and a spherical rod end threaded into the tubular member at one end and connected to the actuator ring at its opposite end.
  • the intermediate member has a head engaging the bridge of the clevis and a nut threaded onto its outer surface to clamp the clevis bridge against this head and thereby lock the intermediate member relative to the clevis.
  • the intermediate member is also fiatted so that a wrench may be employed to rotate it, when the check nut is loosened to vary the extent to which the rod end is threaded therein and thus adjust the effective length of the link.
  • the pivotal connection for the clevis comprises a ball journaled in the web of the control lever and a pin extending through the arms of the clevis and the ball.
  • Bosses extend inwardly from the clevis arms to engage the ball and position the clevis laterally of the control lever.
  • the flanges of the control lever are slotted adjacent one end thereof to permit assembly of the clevis thereon without any substantial effect on the strength of the lever itself.
  • FIG. 1 is an elevation of a gas turbine engine comprising an axial flow compressor having control mecha nism embodying the present invention
  • FIG. 2 is an enlarged elevation, with portions broken away and in section, of the axial flow compressor seen in FIG. 1;
  • FIG. 3 is a section taken on line III-III in FIG. 2;
  • FIG. 4 is a section, on an enlarged scale taken on line IVIV in FIG. 2;
  • FIG. 5 is a perspective view of a pivotal connector piece
  • FIG. 6 is a section taken on line VIVI in FIG. 2;
  • FIG. 7 is an exploded view showing means for guiding one end of a control lever seen in FIG. 2;
  • FIG. 8 is a view illustrating, in section, the connection of an actuator to this end of the control lever.
  • FIG. 1 shows a gas turbine engine l of a type in which the present invention may be advantageously incorporated.
  • Air entering the front end of the engine is compressed by an axial flow compressor 12 to provide the proper air pressure for supporting combustion of fuel within a combustor section 14-.
  • the combustion products are discharged through a turbine (not shown) which drives a rotor (identified below) of the axial flow compressor.
  • the energy level of the combustion products may be augmented by the further combustion of fuel in an afterburner 16 and discharged therefrom to provide a propulsive force, as when the engine It is used in the propulsion of an aircraft.
  • the present invention is directed to improvements pertaining to axial flow compressors and that the gas turbine engine could take other forms.
  • the compressor comprises a plurality of stages with each stage being formed by a circumferential row radially disposed stator blades 17 lying in a given plane and mounted on a cylindrical casing 18, which stator blades cooperate with a circumferential row of rotor blades 19 lying in an adjacent plane and mounted on a rotor 28.
  • the stators of at least the initial stages of the compressor be pivotally adjusted about axes radial of the compressor casing axis during operation of the engine.
  • each of the adjustable stators has a stub shaft 22 at its outer end which is journaled (FIGS. 2 and by appropriate means in the compressor casing 20.
  • the inner ends of each of the stators 17 is appropriately journaled by means supported from the compressor casing (not shown). It is desired that each of the stators 17 of a given stage be simultaneously pivoted about the axis of the stub shaft 22.
  • levers 24 having a common effective length are secured to the stub shafts 22.
  • All of the levers 24 for a given stage are connected at their outer ends by means later described in detail to an actuator ring 26 which is mounted for oscillatory movement on the casing 18.
  • Each of the rings 26 is connected by a link 28 to a control lever 38.
  • Preferably two levers 30 are employed on opposite sides of the easing 18 with appropriate connections being made thereto. However, only one lever 30 is shown and the description thereof will apply to the other lever.
  • the lever 30 is pivotally mounted at one end on a pin 3-2 projecting from a bracket 34 affixed to the compressor casing U8.
  • the opposite end of the lever 30 is connected to the piston rod 36 of an actuator 38 (best seen in FIG. 1).
  • One end of the actuator 38 is pivotally mounted at 40 on the compressor 12.
  • the outer end of the lever 30 to which the rod 36 is attached is guided for reciprocable or oscillating movement in a fixed plane by the means now to be described.
  • a stud 4-2 projects from the outer end of the lever 38 and carries a spherical journal member 44 which is part of a rod end 46 secured to the piston rod 36, all of which is assembled on the stud 42 before it is secured to the lever 38.
  • a pair of lugs 48 are formed on the outer end of the stud and are received by slots 50 in a guide piece 52 which is rotated 90 from its disassembled position seen in FIG 7, after being telescoped onto the stud 42. The guide piece 52 is thus locked on the stud 42 when the guide piece is positioned within a channel 54, formed on a bracket 56 which is secured to the compressor casing 18.
  • the actuator 38 may be controlled by known servo control means, responsive to engine control signals, to position the lever 38 and thereby simultaneously adjust the angular position of all the stators 17 of each of the adjustable stator stages.
  • the extent of pivotal movement imparted to each of the stators of a given stage can be controlled by the preselected length of the lever arms 24 and to some extent adjusted by varying the effective length of the various links 28.
  • a cable 55 secured to the control lever 38 by a further link 28 provides a position feedback function usual in closed loop controls.
  • the links 28 be able to freely transmit movement between the lever 30 which is oscillated (by actuator 38) in a plane tangent to the actuator rings 26 whereas the actuator rings oscillate about the axis of the compressor and are displaced axially thereof as the lever arms 24 in turn oscillate about the axes of the stub shafts 22. It is further desirable that the effective lengths of the links 28 be accurately adjustable. Combined with these desired results it is essential for aircraft operation that the overall construction be extremely light weight.
  • the rod end 62 is secured to the actuator ring 26 by a shoulder screw 64 so that universal movement can be had between the link 28 and the actuator ring 26.
  • the upper end of the link 28 is secured to the lever 30 by a pin 66 which passes through a spherical journal member 68, captured in the vertical web of the lever 30.
  • the clevis 58 has inwardly projecting bosses 70 which engage the flatted ends of the spherical journal member 68 to accurately position the clevis 58, relative thereto and thereby provide for universal movement of the link 28 relative to the lever 30.
  • the intermediate member 60 is provided with a head 72 at its upper end, which bottoms against the bridge of the clevis 58 as the lower portion of the adjusting link extends through an opening therein.
  • the outer surface of the intermediate member 60 is threaded so that a nut 74 may be threaded thereon to clamp the intermediate member relative to the clevis 58.
  • the intermediate member 60 is also interiorly threaded to receive the rod end 62, and a check nut 76 is provided to clamp the rod end relative thereto.
  • the outer surface of the intermediate member 60 is flatted at 78 so that a wrench may be appiled thereto. Tus by slightly loosening the nuts 74 and 76 it is possible to rotate the intermediate member 60 and thereby vary the extent to which the rod end 62 is threaded therein, and in turn adjust the effective length of the link 28.
  • the ring is compositely formed by a pair of arcuate segments 80 having an included angle somewhat less than 180 and joined together at their opposite ends by a connector 82.
  • the segments 80 are advantageously of a square tubular cross section, as best seen in FIG. 4.
  • the connectors 82 are secured thereto by the screws 84 and maintained in spaced relation from the sections 80 by collars 86. Pins 88 serve to accurately position the connectors 82 relative to the segments 80.
  • the stators 17 of a given stage may be very closely spaced in an angular sense, one from another, and the levers 24 secured thereto will therefore extend not only to the segments but to the connector 82 and also between the segment 80 and connector 82 as can be seen in FIGS. 2 and 4.
  • levers 24 (FIGS 4-6) and the actuator ring 26 uniquely accommodates any one of these situations.
  • the levers 24 are relatively thin, flat, and therefore can be reversible.
  • a pin 90 is secured to the outer end of each lever 24 and is disposed radially of the compressor casing 18 when the lever 24 is aligned with the casing axis, as illustrated in FIG. 4.
  • the pin 90 is telescoped into a bushing 92 which is secured in the ring 26.
  • the bushing 92 is preferably formed of polytetrafluoroethylene impregnated with glass fibers and has a head 94 on one end which limits the extent to which it may be telescoped through holes 96 in the outer surfaces of the segments 80 and inner surfaces of the connectors 82.
  • the outer end of the sleeve 92 (FIG. 5 is fiatted and passes through slots formed either on the inner surfaces of the segments 80 or the outer surface of the connectors 82. Beads are formed on the flatted outer end portions of the inserts 92 to provide detent means for releasably holding the inserts on either the segments 80 or connectors 82.
  • the levers 24 connected to the segments 80 are preferably preflexed outwardly a slight amount and the levers 24 connected to the connectors 82 are flexed inwardly a slight amount so that the actuator ring in fact is positioned thereby on the compressor.
  • thrust buttons 102 are secured to the outer ends of selected inserts 92 and held thereon by cotter pins 1%.
  • the thrust buttons 1&2 engage bearing pads 106 formed on the casing 18.
  • inwardly projecting bosses '70 of the clevis 53 can be slid through slots 108 and 110 formed in the bottom reinforcing rib of the lever 30. These slots are provided at both ends of the lever for ease of assembly. This can best be seen in FIGS. 2 and 3.
  • stator blades of at least the initial stages being pivotal about axes radial of the rotor axis
  • stator adjustment mechanism comprising a relatively thin lever secured to each stator and extending in a plane normal to the plane of that stator,
  • each actuator ring comprising a pair of arcuate seg ments of square tubular cross section and connectors, in part tubular, overlapping the segments, spaced outwardly therefrom and secured thereto to compositely form a ring,
  • each of the levers having a pin projecting from the plane thereof
  • said segments having openings in the outer walls thereof and aligned circumferential slots in their inner walls,
  • said connectors having holes in their inner walls and aligned circumferential slots in their outer walls, inserts formed of polytetrafluoroethylene impregnated with glass fibers, said inserts being generally tubular in form and having a head at one end and being flatted at their opposite end with beads adjacent the terminus of the opposite end, said inserts being compressor 6 telescoped through the holes in said segments and connectors with their flattend ends being received by said slots and with the inserts retained on said segments and connectors by the heads and beads thereon,
  • said compressor casing having formed thereon bearing pads engaged by said thrust buttons to accurately :position the actuating rings relative to said compressor casing
  • control lever of I-shaped cross section pivotally mounted at one end on the compressor casing and guided at its opposite end for movement in a flat plane
  • each adjustable link comprising a clevis connected to the control lever
  • said intermediate member being threaded on its outer and inner surfaces
  • each adjustable link comprising a ball journaled in the vertical Web of the control lever and a pin passing through the arms of the clevis and the ball,
  • said clevis having inwardly extending bosses to position the adjusting link relative to the ball
  • the flange of said control lever being notched on opposite sides of its web and adjacent one end thereof to facilitate assembly of the clevises thereon.
  • stator blades of at least the initial stages being pivotal about axes radial of the rotor axis
  • stator adjustment mechanism comprising a relatively thin lever secured to each stator and extending in a plane normal to the plane of that stator,
  • each actuator ring comprising a pair of arcuate segments of square tubular cross section and connectors, in part tubular, overlapping the segments, spaced outwardly therefrom and secured thereto to compositely form a ring,
  • each of the levers having a pin projecting from the plane thereof said segments having openings in the outer Walls thereof and aligned circumferential slots in their inner walls, said connectors having holes in their inner walls and aligned circumferential slots in their outer walls, inserts formed of polytetrafluoroethylene impregnated with glass fibers, said inserts being generally tubular in form and having a head at one end and being flatted at their opposite end with with beads adjacent the terminus of the opposite end, said inserts being telescoped through the holes in said segments and connectors with their flatted ends being received by said slots and with the inserts retained on said segments and connectors by the heads and beads thereon, the pins on said levers being pivotally received by the inserts to synchronize movement of all of the stators of each stage, selected and arcuately spaced inserts projecting through said segments, having thrust buttons telescoped over their lower ends, said compressor casing having formed thereon bearing pads engaged by said thrust buttons to accurately position the actuating rings relative to said compressor casing, and means for simultaneously
  • stator blades of at least the initial stages being pivotal about axes radial of the rotor axis
  • stator adjustment mechanism comprising a lever secured to each stator and extending in a plane normal to the plane of that stator, an actuator of tubular form ring for each row of stators, at least a portion of the levers of each row extending into overlying relation with the ring, each of the levers having a pin projecting from the plane thereof, said rings having openings in the outer falls thereof and aligned circumferential slots in their inner walls, inserts formed of polytetrafluoroethylene impregnated with glass fibers, said inserts being generally tubular in form and having a head at one end and being fiatted at their opposite end, said inserts being telescoped through the openings in said rings with their fiatted ends being received by said slots, the pins on said levers being pivotally received by the respective inserts to synchronize movement of all of the stators of each stage, and means for simultaneously oscillating said actuator rings to thereby adjust the stators in accordance with the operating conditions of the compressor.
  • stator blades of at least the initial stages being pivotal about axes radial of the rotor axis
  • stator adjustment mechanism comprising a relatively thin lever secured to each stator and extending in a plane normal to the plane of that stator, an actuator ring for each row of stators,
  • control lever of I-shaped cross section pivotally mounted at one end on the compressor casing and guided at its opposite end for movement in a fiat plane
  • each adjustable link comprising a clevis connected to the control lever
  • said intermediate member being threaded on its outer and inner surfaces
  • each adjustable link comprising a ball journaled in the vertical web of the control lever and a pin passing through the arms of the clevis and the ball,
  • said clevis having inwardly extending bosses to position the adjusting link relative to the ball
  • the flange of said control lever being notched on opposite sides of its web and adjacent one end thereof to facilitate assembly of the clevises thereon.
  • stator blades of at least the initial stages being pivotal about axes radial of the rotor axis
  • stator adjustment mechanism comprising a relatively thin lever secured to each stator and extending in a plane normal to the plane of that stator,
  • control lever of I-shaped cross section pivotally mounted at one end on the compressor casing and guided at its opposite end for movement in fiat plane
  • each adjustable link comprising a clevis connected to the control lever
  • said intermediate member being threaded on its outer and inner surfaces
  • the lower end of said intermediate member being flatted so that a wrench may be applied thereto and with the check nut loosened, the intermediate member rotated to adjust the extent to which the rod end is threaded therein, thereby adjusting the eifective length of the link.
  • stator blades of at least the initial stages being pivotal about axes radial of the rotor axis
  • stator adjustment mechanism comprising a plurality of actuating rings circumferentially surrounding the compressor casing, each actuating ring being offset axially from a respecive row of pivoted stator blades,
  • control lever pivotally mounting said control lever to the compressor casing for movement in a flat plane, and actuating means connected to said control lever for oscillating said control lever within said plane
  • Stator adjusting mechanism as defined by claim 6 in which the means for pivotally connecting each of said levers to the respective actuating means comprises:
  • said pin may pivot Within said tubular insert and move along said axis.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US462688A 1965-06-09 1965-06-09 Adjustment mechanism for axial flow compressors Expired - Lifetime US3314595A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US462688A US3314595A (en) 1965-06-09 1965-06-09 Adjustment mechanism for axial flow compressors
FR85071A FR1501627A (fr) 1965-06-09 1966-11-25 Mécanisme de réglage pour les compresseurs à écoulement axial
BE691934D BE691934A (enrdf_load_stackoverflow) 1965-06-09 1966-12-29

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US462688A US3314595A (en) 1965-06-09 1965-06-09 Adjustment mechanism for axial flow compressors

Publications (1)

Publication Number Publication Date
US3314595A true US3314595A (en) 1967-04-18

Family

ID=23837403

Family Applications (1)

Application Number Title Priority Date Filing Date
US462688A Expired - Lifetime US3314595A (en) 1965-06-09 1965-06-09 Adjustment mechanism for axial flow compressors

Country Status (2)

Country Link
US (1) US3314595A (enrdf_load_stackoverflow)
BE (1) BE691934A (enrdf_load_stackoverflow)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3458118A (en) * 1967-08-21 1969-07-29 Gen Electric Low profile stator adjusting mechanism
US3685920A (en) * 1971-02-01 1972-08-22 Gen Electric Actuation ring for variable geometry compressors or gas turbine engines
DE2618727A1 (de) * 1975-05-01 1976-11-11 Rolls Royce 1971 Ltd Einrichtung zur verstellung des schaufelanstellwinkels eines verdichterleitschaufelkranzes einer turbomaschine
DE3124409A1 (de) * 1980-06-28 1982-02-25 Rolls-Royce Ltd., London "vorrichtung zur leitradverstellung bei turbomaschinen"
US4755104A (en) * 1986-04-29 1988-07-05 United Technologies Corporation Stator vane linkage
US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
US5549448A (en) * 1995-02-08 1996-08-27 United Technolgies Corporation Variable stator vane linkage system and method
US5993152A (en) * 1997-10-14 1999-11-30 General Electric Company Nonlinear vane actuation
US6092984A (en) * 1998-12-18 2000-07-25 General Electric Company System life for continuously operating engines
US6471471B1 (en) * 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US6821084B2 (en) 2002-12-11 2004-11-23 General Electric Company Torque tube bearing assembly
US20060001094A1 (en) * 2003-05-21 2006-01-05 Micron Technology, Inc. Semiconductor on insulator structure
US20120087780A1 (en) * 2008-06-12 2012-04-12 Suciu Gabriel L Integrated actuator module for gas turbine engine
DE102012007129A1 (de) * 2012-04-10 2013-10-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
EP2481891A3 (en) * 2011-02-01 2013-12-18 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US20160348530A1 (en) * 2013-12-19 2016-12-01 Scnema Turbine engine compressor, in particular of an aeroplane turboprop or turbofan
US20170122338A1 (en) * 2015-11-04 2017-05-04 General Electric Company Turnbuckle dampening links
US9856744B2 (en) * 2012-05-04 2018-01-02 Borgwarner Inc. Bayonet spacer retention system for variable turbine geometry vane packs
US20180313222A1 (en) * 2017-04-27 2018-11-01 General Electric Company Variable stator vane actuator overload indicating bushing
US20190024531A1 (en) * 2017-07-19 2019-01-24 Rolls-Royce Plc Unison ring assembly
EP3460201A3 (en) * 2017-09-25 2019-06-05 Rolls-Royce plc Variable stator vane rigging
US10352187B2 (en) * 2016-09-01 2019-07-16 Rolls-Royce Plc Variable stator vane rigging
US20190218929A1 (en) * 2016-05-25 2019-07-18 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
US10519798B2 (en) * 2016-09-22 2019-12-31 Rolls-Royce Plc Gas turbine engine with variable guide vanes and a unison ring
US20230287800A1 (en) * 2022-03-10 2023-09-14 General Electric Company Device for fixing position of adjustable rows of guide vanes of turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2371706A (en) * 1941-02-10 1945-03-20 Eugene Andre Paul Axial flow compressor
US2842305A (en) * 1955-11-01 1958-07-08 Gen Electric Compressor stator assembly
US2933235A (en) * 1955-01-11 1960-04-19 Gen Electric Variable stator compressor
US3056541A (en) * 1958-03-26 1962-10-02 Bristol Siddeley Engines Ltd Adjustable pitch guide blades

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2371706A (en) * 1941-02-10 1945-03-20 Eugene Andre Paul Axial flow compressor
US2933235A (en) * 1955-01-11 1960-04-19 Gen Electric Variable stator compressor
US2842305A (en) * 1955-11-01 1958-07-08 Gen Electric Compressor stator assembly
US3056541A (en) * 1958-03-26 1962-10-02 Bristol Siddeley Engines Ltd Adjustable pitch guide blades

Cited By (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3458118A (en) * 1967-08-21 1969-07-29 Gen Electric Low profile stator adjusting mechanism
US3685920A (en) * 1971-02-01 1972-08-22 Gen Electric Actuation ring for variable geometry compressors or gas turbine engines
DE2618727A1 (de) * 1975-05-01 1976-11-11 Rolls Royce 1971 Ltd Einrichtung zur verstellung des schaufelanstellwinkels eines verdichterleitschaufelkranzes einer turbomaschine
DE3124409A1 (de) * 1980-06-28 1982-02-25 Rolls-Royce Ltd., London "vorrichtung zur leitradverstellung bei turbomaschinen"
US4430043A (en) 1980-06-28 1984-02-07 Rolls-Royce Limited Variable stator vane operating mechanism for turbomachines
US4755104A (en) * 1986-04-29 1988-07-05 United Technologies Corporation Stator vane linkage
US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
US5549448A (en) * 1995-02-08 1996-08-27 United Technolgies Corporation Variable stator vane linkage system and method
US5993152A (en) * 1997-10-14 1999-11-30 General Electric Company Nonlinear vane actuation
US6092984A (en) * 1998-12-18 2000-07-25 General Electric Company System life for continuously operating engines
US6471471B1 (en) * 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US6821084B2 (en) 2002-12-11 2004-11-23 General Electric Company Torque tube bearing assembly
US20060001094A1 (en) * 2003-05-21 2006-01-05 Micron Technology, Inc. Semiconductor on insulator structure
US7528463B2 (en) 2003-05-21 2009-05-05 Micron Technolgy, Inc. Semiconductor on insulator structure
US20120087780A1 (en) * 2008-06-12 2012-04-12 Suciu Gabriel L Integrated actuator module for gas turbine engine
US9097137B2 (en) * 2008-06-12 2015-08-04 United Technologies Corporation Integrated actuator module for gas turbine engine
US8794910B2 (en) 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
EP2481891A3 (en) * 2011-02-01 2013-12-18 United Technologies Corporation Gas turbine engine synchronizing ring bumper
EP2824286A1 (en) * 2011-02-01 2015-01-14 United Technologies Corporation Gas turbine engine synchronizing ring bumper
DE102012007129A1 (de) * 2012-04-10 2013-10-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
US9797265B2 (en) 2012-04-10 2017-10-24 Rolls-Royce Deutschland Ltd & Co Kg Stator vane adjusting device of a gas turbine
US9856744B2 (en) * 2012-05-04 2018-01-02 Borgwarner Inc. Bayonet spacer retention system for variable turbine geometry vane packs
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US10590794B2 (en) * 2013-12-19 2020-03-17 Safran Aircraft Engines Turbine engine compressor, in particular of an aeroplane turboprop or turbofan
US20160348530A1 (en) * 2013-12-19 2016-12-01 Scnema Turbine engine compressor, in particular of an aeroplane turboprop or turbofan
US20170122338A1 (en) * 2015-11-04 2017-05-04 General Electric Company Turnbuckle dampening links
US9982686B2 (en) * 2015-11-04 2018-05-29 General Electric Company Turnbuckle dampening links
US20190218929A1 (en) * 2016-05-25 2019-07-18 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
US10837308B2 (en) * 2016-05-25 2020-11-17 Safran Aircraft Engines Device for controlling variable-pitch members in a turbomachine
US10352187B2 (en) * 2016-09-01 2019-07-16 Rolls-Royce Plc Variable stator vane rigging
US10519798B2 (en) * 2016-09-22 2019-12-31 Rolls-Royce Plc Gas turbine engine with variable guide vanes and a unison ring
US20180313222A1 (en) * 2017-04-27 2018-11-01 General Electric Company Variable stator vane actuator overload indicating bushing
US10753224B2 (en) * 2017-04-27 2020-08-25 General Electric Company Variable stator vane actuator overload indicating bushing
US20190024531A1 (en) * 2017-07-19 2019-01-24 Rolls-Royce Plc Unison ring assembly
US10718230B2 (en) * 2017-07-19 2020-07-21 Rolls-Royce Plc Unison ring assembly
EP3460201A3 (en) * 2017-09-25 2019-06-05 Rolls-Royce plc Variable stator vane rigging
US20230287800A1 (en) * 2022-03-10 2023-09-14 General Electric Company Device for fixing position of adjustable rows of guide vanes of turbomachine
US11920482B2 (en) * 2022-03-10 2024-03-05 General Electric Company Device for fixing position of adjustable rows of guide vanes of turbomachine

Also Published As

Publication number Publication date
BE691934A (enrdf_load_stackoverflow) 1967-06-29

Similar Documents

Publication Publication Date Title
US3314595A (en) Adjustment mechanism for axial flow compressors
US2999630A (en) Compressor
US3990809A (en) High ratio actuation linkage
US4430043A (en) Variable stator vane operating mechanism for turbomachines
US6769868B2 (en) Stator vane actuator in gas turbine engine
US3873230A (en) Stator vane actuating mechanism
US3487992A (en) Stator adjusting mechanism for axial flow compressors
US5466122A (en) Turbine engine stator with pivoting blades and control ring
JP5911863B2 (ja) ターボ機械の枢動羽根を制御するための装置
US10626747B2 (en) Variable vane actuation arrangement
US5795128A (en) Control device for a pivot integrated in a manifold
US11248560B2 (en) Linkage assembly preventing axial rotation of the link rod for a gas turbine engine
US2842305A (en) Compressor stator assembly
US11092167B2 (en) Variable vane actuating system
US3954349A (en) Lever connection to syncring
GB1368353A (en) Actuation ring for variable geometry axial flow compressors
US4373859A (en) Unison ring support system
US20140010637A1 (en) Torque box and linkage design
US3502260A (en) Stator vane linkage for axial flow compressors
JP6743028B2 (ja) タービンエンジンの可変ピッチベーンを制御するためのシステム
US3029067A (en) Variable area nozzle means for turbines
US3574479A (en) Turbine having variable-angle nozzle guide vanes
US2932440A (en) Compressor blade adjustment means
US3841790A (en) Compressor flow fence
US11092032B2 (en) Variable vane actuating system