US3487992A - Stator adjusting mechanism for axial flow compressors - Google Patents

Stator adjusting mechanism for axial flow compressors Download PDF

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US3487992A
US3487992A US679866A US3487992DA US3487992A US 3487992 A US3487992 A US 3487992A US 679866 A US679866 A US 679866A US 3487992D A US3487992D A US 3487992DA US 3487992 A US3487992 A US 3487992A
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stator
casing
actuator
compressor
axial flow
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US679866A
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Urbano A Pineda
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General Electric Co
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General Electric Co
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    • 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 disclosure shows an axial flow compressor comprising a casing, a rotor therein, airfoil blades mounted in circumferential rows alternately on the rotor andthe casing.
  • the blades of a plurality of the 4,stator rows, mounted on the casing, are pivotal about axes radial of the rotor.
  • Each of the pivotal blades in a given row is connected to a unison ring.
  • the unison rings are respectively connected, by links, to lever arms which project from a distributor shaft.
  • the distributor shaft is mounted on the casing longitudinally thereof.
  • a single, reciprocable actuator has one end mounted ⁇ on the casing and its opposite end connected toa lever arm' projecting from the distributor shaft. Movement of the actuator simultaneously adjusts all of the pivotal stator blades to properly control air ow through the compressor.
  • the present invention relates to improvements in gas turbine engines, and, more particularly, to improvements in variable geometry axial flow compressors used in such engines.
  • Axial flow compressors comprise a rotor having a plurality of circumferential rows of airfoil blades spaced along its length. Relatively stationary rows of stator vanes are mounted on the compressor casing betweenthe rows of rotor blades, with each adjacent. pair of rotor and stator blades forming a compressor stage.
  • stator actuation systemv which is extremely rugged, with a long-wear life, consistent with the desire to eliminate or greatly protract the time between engine overhauls in which the engine is thoroughly inspectedend rebuilt in many respects.
  • the obvious approach to increasing ruggedness by increasing the size of components is at odds with the strong motivation to reduce weight in aircraft installations.
  • the compressor casing is desirably a thinwalled shell not particualrly suited to external force loadings thereon.
  • the compressor casing must be sufficiently thick to prevent deection which would cause the stators mounted thereon from being displaced in a mauner adversely affecting compressor operation.
  • stator actuation systems Another aspect of stator actuation systems is the everincreasing demand that the angular adjustment of the stator blades be extremely accurate in order to obtain more eflicient compressor operation. Not only is accuracy desired in the initial installation, but, again looking to the objective of long service life, accuracy must be maintained for prolonged periods of operation.
  • the object of the present invention is, therefore, to provide an improved actuation system for adjusting stators in axial flow compressors and, in doing so, to fulfill the needs outlined above to obtain improved reliability, accuracy, and ruggedness.
  • an axial flow compressor comprising a casing having a rotor therein. Airfoil blades are mounted in circumferential rows alternately on the rotor casing. The blades of a plurality of the rows mounted on the casing are pivotal about axes radial of the rotor.
  • Stator adjusting mechanism is provided which comprises a reciprocable actuator, one end of which is mounted in fixed relation to the casing for movement of its opposite end in a plane generally normal to the rotor axis.
  • An axially extending distributor shaft has a plurality of lever arms projecting radially therefrom with the movable end of the actuator being connected to one of the lever arms.
  • Linkage means connect each of the other lever arms to a given row of pivotal stator blades and provide for simultaneously adjusting all of the stator blades in reponse to movement of the actuator.
  • FIGURE l is a view in outline form of a gas turbine engine in which the present invention is embodied;
  • FIGURE 2 is a perspective view illustrating control mechanism seen in FIGURE l;
  • FIGURE 3 is an elevation of this actuator mech ⁇ anism
  • FIGURE 4 is a section taken on line IV-IV of FIGURE 3;
  • FIGURE 5 is a section taken on line V-V of FIG- URE 3.
  • FIGURE 6 is a section taken on line VI-VI in FIGURE 3.
  • FIGURE 1 shows a gas turbine engine 10 of a type normally employed in the propulsionof aircraft. Air enters the engine 10 at 12 and is pressurized by a compressor 14 to support combustion of fuel in a combustor section 16 for the generation of a hot gas stream which is discharged from a nozzle 18 to provide a propulsive force.
  • the compressor 14 is itself of known axial flow type, the internal details of which are not shown herein or necessary for an understanding of the present invention.
  • Such compressors comprise a rotor having circumferential rows of airfoil blades axially spaced along its length. Between each row of rotor blades is a row of stator blades which are mounted on the compressor so that they may be adjusted about axes radial of the main axis. of the compressor.
  • the last ve rows of stators are adjustable in this fashion to provide optimum compressor operation under varying operating conditions.
  • a unison ring 22 encircles the compressor casing adjacent each row of adjustable stators (FIGS. 2 and 6).
  • the several stators of each circumferential row have levers 24 secured thereto which are appropriately connected to the adjacent unison ring 22 by appropriate means which permit universal movement between the point of connection to the rings and the point of connection of the lever arms to the stators.
  • a bracket 26 (FIGS. 2 and 4) is secured to each of the unison rings and is connected to a distributor shaft 28 by a link 30 extending between the bracket 26 and a lever arm 32 projecting from the shaft 28.
  • the connections between the link 30 and the bracket 26 and lever arm 32 are preferably made of spherical connections, such as a ball and socket, to permit universal movement between the link 30 and the bracket 26 and lever arm 32.
  • the links 30 are preferably turnbuckles to enable accurate initial setting of the stator blade angles.
  • the torque shaft 28 is journaled on brackets 34 secured to the casing 20.
  • the journals for the shaft 28 are of the spherical, self-aligning type to facilitate installation of the shaft on the compressor casing.
  • the rod end 36 of an actuator 38 is connected to a lever arm 40, projecting from the distributor shaft 28.
  • the opposite or cylinder end of the actuator 38 is connected to a bracket 42 which is secured to the compressor casing 20.
  • the actuator 38 has appropriate hydraulic connections which direct pressurized fluid to one end or the other of the actuator to cause reciprocation of the piston end 36.
  • connections of the actuator to the bracket 42 and the lever arm 40 are preferably of the spherical type, employing balls and sockets.
  • the described arrangement provides a minimum of connection points between the power source, i.e., the actuator 38 and the stators which are to be adjusted.
  • the actuator may be disposed in essentially tangential relationship to the compressor casing and thus minimize the space envelope required for the stator adjusting mechanism.
  • linkage mechanism for the transmission of all forces en- ⁇ ables all of the connections to be made by way of spherical connections or spherical mountings as in the case of the journals for the shaft 28, thereby insuring a high demanufaeturingv-costs.2
  • an axial flow compressor comprising a casing, a rotor therein and airfoil blades mounted in circumferential rotating and stator rows alternately on said rotor and casing, the blades o f a plurality of stator rows, mounted on Athe casing, being pivotal about axes radial ofthe rotor; l
  • stator adjusting mechanism including ya reciprocahle actuator, one end of which is mounted in xed relation on the casing for movement of its opposite end in a plane generally normal to the rotor axls, ,anaxially extending V.distributor shaft having a plural- ⁇ l :ity of bell cranks projecting radially therefrom,
  • linkage means comprise a unison ring associated with each row of pivotal vstators, lever means connecting individual stators to the adjacent unison ring and a link'connecting each unison ring respectively to one of said other bell cranks.
  • Stator adjusting mechanism as in claim 1 wherein, the reciprocable actuator is disposed substantially tanvgentially of said casing.
  • Stator adjusting mechanism as in claim 2 wherein, spherically-mounted journals are provided for said dis- .tributor shaft and spherical connections are provided for connecting thel reciprocal actuator to the casing f 'and distributor shaft and spherical connections are -provided between said links and said other bell cranks and said unison rings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

2 Sheets-Sheet 1 U. A. PINEDA STATOR ADJUSTING MECHANISM FOR AXIAL FLOW coMPREssoRs Filed Nov. l, 1967 Jan. 69 1970 u. A. PINEDA 3,487,992
STATOR ADJUSTING MECHANISM FOR AXIAL FLOW COMPRESSORS Filed Nov. 1, 1967 2 sheets-sheet z United States Patent O U.S. Cl. 230--114 3 Claims ABSTRACT OF THE DISCLOSURE The disclosure shows an axial flow compressor comprising a casing, a rotor therein, airfoil blades mounted in circumferential rows alternately on the rotor andthe casing. The blades of a plurality of the 4,stator rows, mounted on the casing, are pivotal about axes radial of the rotor. Each of the pivotal blades in a given row is connected to a unison ring. The unison rings are respectively connected, by links, to lever arms which project from a distributor shaft. The distributor shaft is mounted on the casing longitudinally thereof. A single, reciprocable actuator has one end mounted `on the casing and its opposite end connected toa lever arm' projecting from the distributor shaft. Movement of the actuator simultaneously adjusts all of the pivotal stator blades to properly control air ow through the compressor.
The invention described and claimed in the United States patent application herein resulted from work done under United States Government contract FA-SS-G-.
The United States Governmenthas an irrevocable, non-exclusive license under said application to practice and have practiced the invention claimed herein, including the unlimited right to sublicenseothers to practice and have practiced the claimed invention for any purpose whatsoever. y i
The present invention relates to improvements in gas turbine engines, and, more particularly, to improvements in variable geometry axial flow compressors used in such engines.
Axial flow compressors comprise a rotor having a plurality of circumferential rows of airfoil blades spaced along its length. Relatively stationary rows of stator vanes are mounted on the compressor casing betweenthe rows of rotor blades, with each adjacent. pair of rotor and stator blades forming a compressor stage. One accepted method of insuring proper operation of the compressor undervarying operating conditionsuis to pivotally adjust all or several of the stator rows about axes radial of the compressor axis.
To accomplish such adjustment it is desirable to em ploy a single actuator which is mechanically linked to the several stator stages for their simultaneous movement in accordance with a desired schedule. Several proposals for actuation systems of this type have been made. While many are entirely workable and meet the needs of engines operating at the present time, more advanced engines require significant improvements in such aspects as weight, reliability, and envelope, i.e., the area required for installation of the system on the engine,
To be more specific, other engine components have greatly increased reliability, especially in terms of service life, so that at the present time there is a strong demand for a stator actuation systemv which is extremely rugged, with a long-wear life, consistent with the desire to eliminate or greatly protract the time between engine overhauls in which the engine is thoroughly inspectedend rebuilt in many respects. The obvious approach to increasing ruggedness by increasing the size of components is at odds with the strong motivation to reduce weight in aircraft installations. In considering the matter of weight it must be remembered that the actuator forces for stator adjustment systems must be taken by the cornpressor casing. The compressor casing is desirably a thinwalled shell not particualrly suited to external force loadings thereon. The compressor casing must be sufficiently thick to prevent deection which would cause the stators mounted thereon from being displaced in a mauner adversely affecting compressor operation.
Another aspect of stator actuation systems is the everincreasing demand that the angular adjustment of the stator blades be extremely accurate in order to obtain more eflicient compressor operation. Not only is accuracy desired in the initial installation, but, again looking to the objective of long service life, accuracy must be maintained for prolonged periods of operation.
The object of the present invention is, therefore, to provide an improved actuation system for adjusting stators in axial flow compressors and, in doing so, to fulfill the needs outlined above to obtain improved reliability, accuracy, and ruggedness.
The above objects are attained in an axial flow compressor comprising a casing having a rotor therein. Airfoil blades are mounted in circumferential rows alternately on the rotor casing. The blades of a plurality of the rows mounted on the casing are pivotal about axes radial of the rotor. Stator adjusting mechanism is provided which comprises a reciprocable actuator, one end of which is mounted in fixed relation to the casing for movement of its opposite end in a plane generally normal to the rotor axis. An axially extending distributor shaft has a plurality of lever arms projecting radially therefrom with the movable end of the actuator being connected to one of the lever arms. Linkage means connect each of the other lever arms to a given row of pivotal stator blades and provide for simultaneously adjusting all of the stator blades in reponse to movement of the actuator.
The above and other related objects and features of the invention will be apparent from a reading of the following description of the disclosure found in the accompanying drawings and the novelty thereof pointed out in the appended claims. In the drawings:
FIGURE l is a view in outline form of a gas turbine engine in which the present invention is embodied;
FIGURE 2 is a perspective view illustrating control mechanism seen in FIGURE l;
FIGURE 3 is an elevation of this actuator mech` anism;
FIGURE 4 is a section taken on line IV-IV of FIGURE 3;
FIGURE 5 is a section taken on line V-V of FIG- URE 3; and
FIGURE 6 is a section taken on line VI-VI in FIGURE 3.
FIGURE 1 shows a gas turbine engine 10 of a type normally employed in the propulsionof aircraft. Air enters the engine 10 at 12 and is pressurized by a compressor 14 to support combustion of fuel in a combustor section 16 for the generation of a hot gas stream which is discharged from a nozzle 18 to provide a propulsive force.
The compressor 14 is itself of known axial flow type, the internal details of which are not shown herein or necessary for an understanding of the present invention. Such compressors, however, comprise a rotor having circumferential rows of airfoil blades axially spaced along its length. Between each row of rotor blades is a row of stator blades which are mounted on the compressor so that they may be adjusted about axes radial of the main axis. of the compressor. In the present instance, and for illustrative purposes, the last ve rows of stators are adjustable in this fashion to provide optimum compressor operation under varying operating conditions.
A unison ring 22 encircles the compressor casing adjacent each row of adjustable stators (FIGS. 2 and 6). The several stators of each circumferential row have levers 24 secured thereto which are appropriately connected to the adjacent unison ring 22 by appropriate means which permit universal movement between the point of connection to the rings and the point of connection of the lever arms to the stators.
A bracket 26 (FIGS. 2 and 4) is secured to each of the unison rings and is connected to a distributor shaft 28 by a link 30 extending between the bracket 26 and a lever arm 32 projecting from the shaft 28. The connections between the link 30 and the bracket 26 and lever arm 32 are preferably made of spherical connections, such as a ball and socket, to permit universal movement between the link 30 and the bracket 26 and lever arm 32. The links 30 are preferably turnbuckles to enable accurate initial setting of the stator blade angles.
The torque shaft 28 is journaled on brackets 34 secured to the casing 20. The journals for the shaft 28 are of the spherical, self-aligning type to facilitate installation of the shaft on the compressor casing. The rod end 36 of an actuator 38 is connected to a lever arm 40, projecting from the distributor shaft 28. The opposite or cylinder end of the actuator 38 is connected to a bracket 42 which is secured to the compressor casing 20. The actuator 38 has appropriate hydraulic connections which direct pressurized fluid to one end or the other of the actuator to cause reciprocation of the piston end 36.
The connections of the actuator to the bracket 42 and the lever arm 40 are preferably of the spherical type, employing balls and sockets.
When the rod end of the actuator is displayed (in a plane normal to the axis of rotor rotation) to oscillate the distributor shaft 28, the several stator rows connected thereto, are simultaneously adjusted in a pivotal fashion to properly control air flow through the compressor. The timing of and the means for pressuring the actuator 38 to effect such adjustment is well known to those in the art and not a part of the present invention.
It will be apparent that the described arrangement provides a minimum of connection points between the power source, i.e., the actuator 38 and the stators which are to be adjusted. Further, the actuator may be disposed in essentially tangential relationship to the compressor casing and thus minimize the space envelope required for the stator adjusting mechanism. Additionally, the use of linkage mechanism for the transmission of all forces en-` ables all of the connections to be made by way of spherical connections or spherical mountings as in the case of the journals for the shaft 28, thereby insuring a high demanufaeturingv-costs.2
gree of reliability with a minimum of installation and It will further be noted that' the described tangential relationship of the actuator 38 enables the force loadings on the compressor casing 20 to also be essentially tangential where they are applied to the bracket 42 and the brackets 34.v This'minimizes the deective forces on the compressor casing and 'reduces the mass of the casing required to withstand such actuation forces.
Having thus described the invention, what is claimed as novel and desired `to be secured by Letters Patent of thepUnited States is:
1. In an axial flow compressor comprising a casing, a rotor therein and airfoil blades mounted in circumferential rotating and stator rows alternately on said rotor and casing, the blades o f a plurality of stator rows, mounted on Athe casing, being pivotal about axes radial ofthe rotor; l
stator adjusting mechanism including ya reciprocahle actuator, one end of which is mounted in xed relation on the casing for movement of its opposite end in a plane generally normal to the rotor axls, ,anaxially extending V.distributor shaft having a plural- `l :ity of bell cranks projecting radially therefrom,
the other end'of said actuator being connected to one of said bell cranksto impart rotational movement Y Ato said distributor shaft, and
linkage means comprise a unison ring associated with each row of pivotal vstators, lever means connecting individual stators to the adjacent unison ring and a link'connecting each unison ring respectively to one of said other bell cranks. .2, Stator adjusting mechanism as in claim 1 wherein, the reciprocable actuator is disposed substantially tanvgentially of said casing. 3, Stator adjusting mechanism as in claim 2 wherein, spherically-mounted journals are provided for said dis- .tributor shaft and spherical connections are provided for connecting thel reciprocal actuator to the casing f 'and distributor shaft and spherical connections are -provided between said links and said other bell cranks and said unison rings. v
j References Cited UNITED STATES PATENTS WILLIAM L.'FREEH, Primary Examiner
US679866A 1967-11-01 1967-11-01 Stator adjusting mechanism for axial flow compressors Expired - Lifetime US3487992A (en)

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Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3779665A (en) * 1972-09-22 1973-12-18 Gen Electric Combined variable angle stator and windmill control system
US3873230A (en) * 1974-04-10 1975-03-25 United Aircraft Corp Stator vane actuating mechanism
DE2951963A1 (en) * 1978-12-27 1980-07-17 Gen Electric BLOCK BLADE ACTUATOR
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
US4755104A (en) * 1986-04-29 1988-07-05 United Technologies Corporation Stator vane linkage
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
JP2001200799A (en) * 1999-11-22 2001-07-27 General Electric Co <Ge> Damping torque shaft assembly
JP2002147387A (en) * 2000-11-08 2002-05-22 General Electric Co <Ge> Assembly torque shaft
US6769868B2 (en) 2002-07-31 2004-08-03 General Electric Company Stator vane actuator in gas turbine engine
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
US20120230813A1 (en) * 2011-03-07 2012-09-13 Hitachi, Ltd. Axial-Flow Compressor and Modification Method
US20130084179A1 (en) * 2011-09-30 2013-04-04 Hamilton Sundstrand Corporation Variable vane angular position sensor
US20130323028A1 (en) * 2012-05-31 2013-12-05 United Technologies Corporation Actuator mounted to torque box
US20140030069A1 (en) * 2012-07-26 2014-01-30 Jonathan D. Little Top hat bearing retainer for variable vane actuator
US20140064910A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
RU2559107C2 (en) * 2010-01-28 2015-08-10 Сименс Акциенгезелльшафт Device to adjust adjustable guide vanes
US20170108032A1 (en) * 2015-10-16 2017-04-20 General Electric Company Stepped shaft assembly
US20170122338A1 (en) * 2015-11-04 2017-05-04 General Electric Company Turnbuckle dampening links
US11131323B2 (en) * 2016-03-24 2021-09-28 Raytheon Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears

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US6174130B1 (en) * 1999-06-30 2001-01-16 General Electric Company Movable shaft assembly
FR2928979B1 (en) 2008-03-19 2015-05-01 Snecma DEVICE FOR CONTROLLING AUBES WITH VARIABLE TIMING IN A TURBOMACHINE.
US9890655B2 (en) 2008-09-18 2018-02-13 Siemens Aktiengesellschaft Adjusting device for variable guide vanes and method of operation
GB0911459D0 (en) * 2009-07-02 2009-08-12 Rolls Royce Plc An assembly providing contaminant removal
GB2519551A (en) * 2013-10-24 2015-04-29 Rolls Royce Deutschland A variable stator vane arrangement
CN112855600B (en) * 2019-11-12 2023-02-28 中国航发商用航空发动机有限责任公司 Gas compressor and aircraft engine

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GB968190A (en) * 1959-10-20 1964-08-26 Bbc Brown Boveri & Cie Regulating device for thermal turbo-machines
US3146585A (en) * 1961-09-29 1964-09-01 Gen Electric Turbojet control system for preventing compressor stall due to inlet air disturbances
US3327933A (en) * 1964-08-07 1967-06-27 Bbc Brown Boveri & Cie Apparatus for regulating a turbocompressor
US3376018A (en) * 1966-01-10 1968-04-02 Rolls Royce Vane operating mechanism

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Publication number Priority date Publication date Assignee Title
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
GB968190A (en) * 1959-10-20 1964-08-26 Bbc Brown Boveri & Cie Regulating device for thermal turbo-machines
US3146585A (en) * 1961-09-29 1964-09-01 Gen Electric Turbojet control system for preventing compressor stall due to inlet air disturbances
US3327933A (en) * 1964-08-07 1967-06-27 Bbc Brown Boveri & Cie Apparatus for regulating a turbocompressor
US3376018A (en) * 1966-01-10 1968-04-02 Rolls Royce Vane operating mechanism

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3779665A (en) * 1972-09-22 1973-12-18 Gen Electric Combined variable angle stator and windmill control system
US3873230A (en) * 1974-04-10 1975-03-25 United Aircraft Corp Stator vane actuating mechanism
DE2951963A1 (en) * 1978-12-27 1980-07-17 Gen Electric BLOCK BLADE ACTUATOR
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
US4755104A (en) * 1986-04-29 1988-07-05 United Technologies Corporation Stator vane linkage
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
JP2001200799A (en) * 1999-11-22 2001-07-27 General Electric Co <Ge> Damping torque shaft assembly
US6551057B1 (en) * 1999-11-22 2003-04-22 General Electric Company Damped torque shaft assembly
JP2002147387A (en) * 2000-11-08 2002-05-22 General Electric Co <Ge> Assembly torque shaft
US6457937B1 (en) * 2000-11-08 2002-10-01 General Electric Company Fabricated torque shaft
EP1207271A3 (en) * 2000-11-08 2003-08-06 General Electric Company Fabricated torque shaft
US6769868B2 (en) 2002-07-31 2004-08-03 General Electric Company Stator vane actuator in gas turbine engine
US8435000B2 (en) 2008-03-07 2013-05-07 Rolls-Royce Corporation Variable vane actuation system
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
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
RU2559107C2 (en) * 2010-01-28 2015-08-10 Сименс Акциенгезелльшафт Device to adjust adjustable guide vanes
US9188138B2 (en) 2010-01-28 2015-11-17 Siemens Aktiengesellschaft Device for adjusting variable guide vanes
US20120230813A1 (en) * 2011-03-07 2012-09-13 Hitachi, Ltd. Axial-Flow Compressor and Modification Method
EP2497957B1 (en) * 2011-03-07 2020-11-25 Mitsubishi Power, Ltd. Modification method for an axial-flow compressor
US9903389B2 (en) * 2011-03-07 2018-02-27 Mitsubishi Hitachi Power Systems, Ltd. Axial-flow compressor and modification method
US20130084179A1 (en) * 2011-09-30 2013-04-04 Hamilton Sundstrand Corporation Variable vane angular position sensor
US9039355B2 (en) * 2012-05-31 2015-05-26 United Technologies Corporation Actuator mounted to torque box
EP2855899A4 (en) * 2012-05-31 2016-03-16 United Technologies Corp Actuator mounted to torque box
US9777643B2 (en) 2012-05-31 2017-10-03 United Technologies Corporation Actuator mounted to torque box
US20130323028A1 (en) * 2012-05-31 2013-12-05 United Technologies Corporation Actuator mounted to torque box
US20140030069A1 (en) * 2012-07-26 2014-01-30 Jonathan D. Little Top hat bearing retainer for variable vane actuator
US20140064910A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US20170108032A1 (en) * 2015-10-16 2017-04-20 General Electric Company Stepped shaft assembly
EP3163031A1 (en) * 2015-10-16 2017-05-03 General Electric Company Cranked shaft with cranks to control a variable vane assembly
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
US11131323B2 (en) * 2016-03-24 2021-09-28 Raytheon Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears

Also Published As

Publication number Publication date
FR1586566A (en) 1970-02-20
BE723235A (en) 1969-04-01
GB1178650A (en) 1970-01-21
DE1805942A1 (en) 1969-06-26

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