GB2227527A - A variable stator vane arrangement for an axial flow compressor - Google Patents

A variable stator vane arrangement for an axial flow compressor Download PDF

Info

Publication number
GB2227527A
GB2227527A GB8901569A GB8901569A GB2227527A GB 2227527 A GB2227527 A GB 2227527A GB 8901569 A GB8901569 A GB 8901569A GB 8901569 A GB8901569 A GB 8901569A GB 2227527 A GB2227527 A GB 2227527A
Authority
GB
United Kingdom
Prior art keywords
variable stator
axial flow
vane arrangement
flow compressor
axially extending
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB8901569A
Other versions
GB8901569D0 (en
GB2227527B (en
Inventor
Peter Gordon Graham Farrar
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB8901569A priority Critical patent/GB2227527B/en
Publication of GB8901569D0 publication Critical patent/GB8901569D0/en
Priority to US07/440,362 priority patent/US5044879A/en
Publication of GB2227527A publication Critical patent/GB2227527A/en
Application granted granted Critical
Publication of GB2227527B publication Critical patent/GB2227527B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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

Landscapes

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

Abstract

A plurality of stages of variable stator vanes are operated by respective control rings 34, 36, 38, 40, 42. The vanes in each stage are connected to the control rings 34, 36, 38, 40, 42 by operating levers 44, 46, 48, 50, 52. <??>An axially extending member 64 is connected to each control ring 34, 36, 38, 40, 42 by operating links 54, 56, 58, 60, 62. The member 64 is arranged in a plane substantially tangential to each control ring and is movable in the plane substantially tangential to the control rings to change the pitch of the variable stator vanes. <??>Hydraulic rams 66, 68, ball screw actuators or electric stepper motors are provided to move the member 64, and the actuators may be operated to give proportional, or non proportional movement of the variable stator vanes. A controller 94 may use signals from position detectors 78, 80 positioned on the control rings or position detectors 86, 88 positioned on the hydraulic rams together with compressor parameters to control the positions of the vanes. The member 64 may be inclined to axial direction (Fig. 3), formed with steps (Fig. 4) or curved (Fig. 5) <IMAGE>

Description

1 1 A VARIABLE STATOR VANE ARRANGEMENT FOR AN AXIAL FLOW COMPRESSOR The
present invention relates to a variable stator vane arrangement for an axial flow compressor, particularly an axial flow compressor for gas turbine engines.
Generally in prior art axial flow compressors with several stages of variable stator vanes, at the designed operating condition of the compressor all the stages of variable stator vanes are operating at maximum efficiency and each stage of stator vanes has a surge margin. However, when the compressor is operating at conditions in which the rotational speed of the compressor rotor is lower than the designed rotational speed of the compressor rotor it is necessary to vary the angles of the stator vanes to prevent surge or stall of the compressor. It has been found that in high pressure ratio compressors i.e. pressure ratios of the order of 12 to 1 or more, that the variation of the angles of the stator vanes in the presently accepted manner has tended to make any surge or stall worse.
The presently accepted method of varying the angles of the stator vanes uses a proportional method in which the variable stator vanes in each stage are moved a proportion, or fraction of their full designed angular displacement. The variable stator vanes in each stage are all moved through the same proportion of their full designed angular movement in unison.
Recent advances in axial flow compressors has brought about the requirement for methods of varying the angles of the stator vanes in a non proportional method in which the variable stator vanes in each stage are moved a proportion, or fraction, of their full designed angular displacement, but the variable stator vanes in each stage are moved independently of the other variable stator vanes in the other stages. This method has overcome the problem of surge or stall in axial flow compressors of high pressure ratio when operating at conditions of low rotational speeds of the compressor rotor.
U 2 A third method of varying the angles of the stator vanes is to move the stator vanes in a non proportional method in which the variable stator vanes in each stage are moved a proportion, or fraction, of their full designed angular displacement, but the variable stator vanes in each stage are all moved through different proportions of their designed angular movement in unison.
The present invention seeks to provide a novel variable stator vane arrangement for an axial flow compressor which may be used to give a proportional movement of the variable stator vanes or a non proportional movement of the variable stator vanes.
Accordingly the present invention provides a variable stator vane arrangement for an axial flow compressor comprising a plurality of stages of stator vanes, each stage of stator vanes having a plurality of circumferentially arranged radially extending stator vanes mounted for rotation about their longitudinal axes in a stator structure, a plurality of control rings arranged substantially coaxial with the compressor and surrounding the stator structure, the stator vanes in each stage being connected to a respective one of plurality of control rings by operating levers, each control ring being connected to an axially extending member by an operating link, the axially extending member being movable in a plane substantially tangential to and positioned substantially tangential to each of the control rings such that at least one of the control rings is rotated coaxially of the compressor to change the pitch of the stator vanes in the associated stage of stator vanes.
Actuator means may be arranged to move the axially extending member substantially tangentially to the control rings.
The actuator means may comprise a pair of actuators connected to the axially extending member, the actuators being connected to the axially extending member at axially spaced locations.
i 1 k 3 Stop means may be provided to limit the tangential movement of the axially extending member.
The stop means may comprise a first pair of stop members secured to the stator structure and positioned in the plane tangential to the control rings on either side of a first end of the axially extending member and a second pair of stop members secured to the stator structure and positioned in the plane tangential to the control rings on either side of a second end of the axially extending member.
The axially extending member may be substantially straight.
The axially extending member may be curved such that the axially extending member has portions arranged in planes tangential to each control ring.
The axially extending member may be stepped such that the axially extending member has portions arranged in planes tangential to each control ring.
The actuator means may be hydraulic rams.
The actuator means may be ball screw actuators.
The actuator means may be electric stepper motors.
The actuator means may be movable in unison in the same direction to vary the pitch of the stator vanes in each stage at the same time and to vary the pitch of the stator vanes in each stage through the same proportion of their pitch change movement.
The actuator means may be movable to vary the pitch of the stator vanes in each stage non proportionally.
Position detectors may detect the pitch of the variable stator vanes of at least two of the stages of variable stator vanes, the position detectors producing electrical signals indicative of the pitch of the variable stator vanes, a controller analyses the electrical signals indicative of the pitch of the variable stator vanes to produce control signals to operate the actuator means.
The position detectors may be located on the control rings of the at least two stages of variable stator vanes.
4 The position detectors may be located on the actuator means to determine the position of the actuator means.
The position detectors may be located on the vanes of the at least two stages of variable stator vanes.
The controller may compare detected compressor parameters with predetermined characteristics of the compressor and determines any adjustments necessary to the stages of variable stator vanes to more nearly match the compressor parameters with the predetermined characteristics of the compressor.
The present invention will be more fully described by way of example with reference to the accompanying drawings, in which:- Figure 1 is a partially cut away view of a turbofan gas turbine engine having a variable stator vane arrangement for an axial flow compressor according to the present invention.
Figure 2 is an enlarged view of a part of the variable stator vane arrangement shown in Figure 1.
Figure 3 is a view in the direction of arrow B in Figure 2.
Figure 4 is a view in the direction of arrow B in Figure 2 showing an alternative embodiment.
Figure 5 is a view in the direction of arrow B in Figure 2 showing a further embodiment.
Figure 6 is a sectional view in the direction of arrows A in Figure 1.
A turbofan gas turbine engine 10 is shown in Figure 1 and comprises in axial flow series an air intake 12, a fan assembly 14, a compressor assembly 16, a combustor assembly 18, a turbine assembly 20 and an exhaust nozzle 22. The fan assembly 14 comprises a plurality of fan blades 24 secured to and extending radially from a fan rotor 25. The fan blades 24 and fan rotor 25 are enclosed by a fan easing 26, which partially defines a fan duct 30. The fan casing 26 is secured to the core engine casing by fan duct L.) 5 j 1 outlet guide vanes 28. The fan duct 30 has an exhaust nozzle 32 at its downstream end.
The compressor assembly 16 comprises a number of stages of stator vanes and a number of stages of rotor blades (not shown), the stages of stator vanes and rotor blades are arranged axially alternately. A plurality of the stages of the stator vanes, in this example five stages, are of the variable type. Each of the stages of variable stator vanes comprises a plurality of circumferentially arranged radially extending stator vanes 31. The stator vanes 31 are mounted for rotation about their longitudinal axis in a stator casing 33. A plurality of control rings 34,36,38,40 and 42 are arranged substantially coaxial with the compressor assembly 16, and surround the stator casing 33. The stator vanes 31 in each stage of variable stator vanes are connected to a respective one of the plurality of control rings 34,36,38,40 and 42 by operating levers 44,46,48,50 and 52 respectively which are shown more clearly in Figures 2 and 6.
Each of the control rings 34,36,38,40 and 42 is connected to an axially extending member 64 by operating links 54,56,58,60 and 62 respectively. The operating links 54,56,58,60 and 62 extend substantially tangentially with respect to their associated control rings 34,36,38,40 and 42, and the axially extending member 64 is arranged in planes substantially tangential to the control rings 34,36,38,40 and 42.
A first hydraulic ram 66 and a second hydraulic ram 68 are provided to move the axially extending member 64.. The first and second hydraulic rams 66 and 68 are connected to the axially extending member 64 at axially spaced locations.
The ends 67 and 69 of the axially extending member 64 are positioned between end stop members 70,72 and 74,76 which are arranged in the plane substantially tangential to /C) 6 the control rings. The axially extending member 64 has a slot 65 at the position where the hydraulic ram 68 is connected to the axially extending member 64 to allow some relative movement therebetween.
A position detector 78 is located on the control ring 34 and a position detector 80 is located on the control ring 42, the position detectors 78, 80 detect the pitch or angle setting of the vanes and, are arranged to produce electrical signals which are transmitted to a controller 94 via cables 82,84. A position detector 86 is located on the hydraulic ram 66 and a position detector 88 is located on the hydraulic ram 68, the position detectors 86,88 detect the position of the pistons in the hydraulic rams, and are arranged to produce electrical signal which are transmitted to the controller 94 via cables 90,92.
The controller 94 is arranged to receive various engine parameters, for example air flow through the compressor, pressure ratio across the compressor, and to compare these with the desired characteristics of the engine. The controller 94 also uses the electrical signals from the position detectors to determine the position of the pitch of the vanes in each stage of variable stator vanes, and to determine the position of the pistons in the hydraulic rams. The controller 94 determines any adjustment that is necessary to the stages of variable stator vanes in order to match the engine parameters with the desired characteristics of the engine, and the controller 94 controls the flow of hydraulic fluid to the hydraulic rams 66 and 68.
In operation the axially extending member 64 is moved in the plane substantially tangential to the control rings 34,36,38,40 and 42 to rotate the control rings coaxially of the compressor such that the pitch of the variable stator vanes 31 in the stages of variable stator vanes is varied.
The hydraulic rams 66 and 68 may be moved in unison in the same direction such that there is a proportional 7 movement of the variable stator vanes 31 in each stage. The hydraulic rams 66 and 68 may be moved through various distances such that there is a non proportional movement of the variable stator vanes 31 in different stages. The controller 94 controls the hydraulic fluid to the hydraulic rams 66j68 necessary for these movements. The controller 94 is able to cause all the control rings to rotate in the same direction, or to cause some control rings to rotate in opposite directions. The controller is able to cause predetermined control rings to remain stationary or to be delayed in action before commencing to rotate.
The arrangement of the variable stator vanes, control rings, axially extending member, hydraulic rams and controller enables differential movement of the variable stator vanes, the characteristics of the differential movement are controlled by the control logic of the controller for different operating conditions for example low speed, high speed and different transient rates.
The arrangement is also suitable for varying the stator vanes in a non proportional manner in which the variable stator vanes in each stage are moved a proportion of their full designed angular displacement, but the variable stator vanes in each stage are all moved through different proportions of their designed angular movement in unison.
The controller 94 may use the position detectors 86,88 which detect the positions of the pistons in the hydraulic rams to give an indication of the pitch of the vanes in each stage of variable stator vanes 31. However for greater accuracy the controller 94 uses the position detectors 78,80 which detect the positions of the control rings 34,42 to determine the pitch of the vanes in each stage of variable stator vanes. It may be possible to use position detectors located on more than two control rings. Alternatively to obtain most accuracy the detectors may be located on the vanes themselves in two or more of the ( 1 C_ 8 stages of variable stator vanes. It may be possible to have mixed arrangements of position detectors, for example it may be possible to use position detector 78 on the control ring 34 and position detector 88 on the hydraulic ram 68, or position detector 86 on hydraulic ram 66 and position detector 80 on control ring 42.
It may be possible to use other actuator means for example pneumatic rams, electric stepper motors or ball screw actuators. In each case the controller controls the operation of the actuator means.
Figures 3,4 and 5 show alternative views in the direction of arrow A in Figure 2 of the axially extending member 64. In Figure 3 the axially extending member is substantially straight and the links 54,56,58,60 and 62 connect the axially extending member 64 to the control rings 34,36,38, 40 and 42. The control rings are of decreasing diameter in a downstream direction, and therefor the axially extending member is inclined at an angle to the axial direction. In Figure 4 the axially extending member 64 comprises a number of axially extending portions 65A, 65B,65C,65D and 65E which are arranged offset from each other to form a stepped structure. Each of the portions 65A to 6SE is arranged in a plane substantially tangential to the respective control ring. In Figure 5 the axially extending member is curved such that portions of the axially extending member immediately adjacent each control ring are arranged in planes tangential to the respective control ring. It is also possible for a single axially extending member to comprise suitable combinations of any two, or more of axially straight, curved and stepped portions.
i C.
c 9

Claims (20)

  1. Claims: 1. A variable stator vane arrangement for an axial flow compressor
    comprising a plurality of stages of stator vanes, each stage of stator vanes having a plurality of circumferentially arranged radially extending stator vanes mounted for rotation about their longitudinal axes in a stator structure, a plurality of control rings arranged substantially coaxial with the compressor and surrounding the stator structure, the stator vanes in each stage being connected to a respective one of the plurality of control rings by operating levers, each control ring being connected to an axially extending member by an operating link, the axially extending member being movable in a plane substantially tangential to and positioned substantially tangential to each of the control rings such that at least one of the control rings is rotated coaxially of the compressor to change the pitch of the stator vanes in the associated stage of stator vanes.
  2. 2. A variable stator vane arrangement for an axial flow compressor as claimed in claim 1 in which actuator means are arranged to move the axially extending member substantially tangentially to the control rings.
  3. 3. A variable stator vane arrangement for an axial flow compressor as claimed in claim 2 in which the actuator means comprises a pair of actuators connected to the axially extending member, the actuators being connected to the axially extending member at axially spaced locations.
  4. 4. A variable stator vane arrangement for an axial flow compressor as claimed in claim 1, claim 2 or claim 3 in which stop means are provided to limit the tangential movemeht of the axially extending member.
  5. 5. A variable stator vane arrangement for an axial flow compressor as claimed in claim 4 in which the stop means comprises a first pair of stop members secured to the stator structure and positioned in the plane tangential to the control rings on either side of a first end of the
  6. 6 axially extending member and a second pair of stop members secured to the stator structure and positioned in the plane tangential to the control rings on either side of a second end of the axially extending member. 6. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 5 in which the axially extending member is substantially straight.
  7. 7. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 5 in which the axially extending member is curved, such that the axially extending member has portions arranged in planes tangential to each control ring.
  8. 8. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 5 in which the axially extending member is stepped such that the axially extending member has portion arranged in planes tangential to each control ring.
  9. 9. A variable stator vane arrangement for an axial flow compressor as claimed in claim 2 or claim 3 in which the actuator means are hydraulic rams.
  10. 10. A variable stator vane arrangement for an axial flow compressor as claimed in claim 2 or claim 3 in which the actuator means are ball screw actuators.
  11. 11. A variable stator vane arrangement for an axial flow compressor as claimed in claim 2 or claim 3 in.which the actuator means are electric stepper motors.
  12. 12. A variable stator vane arrangement for an axial flow compressor as claimed in claim 3, claim 9, claim 10 or claim 11 in which the actuator means are movable in unison in the same rotational direction to vary the pitch of the stator vanes in each stage at the same time and to vary the pitch of the stator vanes in each stage through the same proportion of their pitch change movement.
  13. 13. A variable stator vane arrangement for an axial flow compressor as claimed in claim 3, claim 9, claim 10 or j C J c 11 claim 11 in which the actuator means are movable to vary the pitch of the stator vanes in each stage nonproportionally.
  14. 14. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 13 in which position detectors detect the pitch of the variable stator vanes of at least two of the stages of variable stator vanes, the position detectors producing electrical signals indicative of the pitch of the variable stator vanes, a controller analyses the electrical signals indicative of the pitch of the variable stator vanes to produce control signals to operate the actuator means.
  15. 15. A variable stator vane arrangement for an axial flow compressor as claimed in claim 14 in which the position detectors are located on the control rings of the at least two stages of variable stator vanes.
  16. 16. A variable stator vane arrangement for an axial flow compressor as claimed in claim 14 in which the position detectors are located on the actuator means to determine the position of the actuator means.
  17. 17. A variable stator vane arrangement for an axial flow compressor as claimed in claim 14 in which the position detectors are located on the vanes of the at least two stages of variable stator vanes.
  18. 18. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 14 to 17 in which the controller compares detected compressor parameters with predetermined characteristics of the compressor and determines any adjustments necessary to the stages of variable stator vanes to more nearly match the compressor parameters with the predetermined characteristics of the compressor.
  19. 19. A variable stator vane arrangement for an axial flow compressor substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
    1) d.
  20. 20. A gas turbine engine comprising a variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 19.
    i Published 1990 at ThePatentOllice,State House, C"]. Holbom,L4)ndonWC1R4TP. Purther copies maybe obtalnedfrom The Patentoffice. Sales Branch, St. Mary Cray, Orpington. Kent BRS 3RD. Printed by Multiplex techniques ltd, St Mary Cray. Kent. Con. 1187
GB8901569A 1989-01-25 1989-01-25 A variable stator vane arrangement for an axial flow compressor Expired - Fee Related GB2227527B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB8901569A GB2227527B (en) 1989-01-25 1989-01-25 A variable stator vane arrangement for an axial flow compressor
US07/440,362 US5044879A (en) 1989-01-25 1989-11-22 Variable stator vane arrangement for an axial flow compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8901569A GB2227527B (en) 1989-01-25 1989-01-25 A variable stator vane arrangement for an axial flow compressor

Publications (3)

Publication Number Publication Date
GB8901569D0 GB8901569D0 (en) 1989-03-15
GB2227527A true GB2227527A (en) 1990-08-01
GB2227527B GB2227527B (en) 1993-06-09

Family

ID=10650551

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8901569A Expired - Fee Related GB2227527B (en) 1989-01-25 1989-01-25 A variable stator vane arrangement for an axial flow compressor

Country Status (2)

Country Link
US (1) US5044879A (en)
GB (1) GB2227527B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2410530A (en) * 2004-01-27 2005-08-03 Rolls Royce Plc Electrically actuated stator vane arrangement
EP2557276A3 (en) * 2011-08-08 2017-04-05 General Electric Company Variable stator vane control system
CN110792621A (en) * 2019-11-08 2020-02-14 江苏科技大学 Double-shaft motor fan assembly structure convenient for heat dissipation
RU2815592C1 (en) * 2023-10-25 2024-03-19 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Axial multistage compressor guide vanes turning mechanism

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
FR2739137B1 (en) * 1995-09-27 1997-10-31 Snecma DEVICE FOR CONTROLLING A VARIABLE SETTING BLADE STAGE
US5622473A (en) * 1995-11-17 1997-04-22 General Electric Company Variable stator vane assembly
FR2856424B1 (en) * 2003-06-20 2005-09-23 Snecma Moteurs DEVICE FOR VARIABLE SETTING OF TWO FLOORS OF BLADES FIXED ON A TURBOJETACTOR
US20050129340A1 (en) * 2003-12-10 2005-06-16 Arnold Robert A. Hourglass bearing
US7096657B2 (en) * 2003-12-30 2006-08-29 Honeywell International, Inc. Gas turbine engine electromechanical variable inlet guide vane actuation system
GB2414047B (en) * 2004-05-14 2006-06-28 Rolls Royce Plc Load absorption arrangements for gas turbine engines
FR2881190A1 (en) * 2005-01-21 2006-07-28 Snecma Moteurs Sa Variable pitch stator guide vane actuating device for e.g. aircraft engine, has actuator fixed to casing and acting on bridge, where device that acts on actuating rings is arranged between rings and does not extend beyond rings
FR2885969B1 (en) * 2005-05-17 2007-08-10 Snecma Moteurs Sa TURBOMACHINE VARIABLE ROTATION ANGLE STATOR AUTONER STAGE CONTROL SYSTEM
US8066474B1 (en) * 2006-06-16 2011-11-29 Jansen's Aircraft Systems Controls, Inc. Variable guide vane actuator
US7758306B2 (en) * 2006-12-22 2010-07-20 General Electric Company Turbine assembly for a gas turbine engine and method of manufacturing the same
EP2165047A1 (en) * 2007-04-10 2010-03-24 Elliott Company Centrifugal compressor having adjustable inlet guide vanes
US9097137B2 (en) * 2008-06-12 2015-08-04 United Technologies Corporation Integrated actuator module for gas turbine engine
US20110210555A1 (en) * 2010-02-26 2011-09-01 Xia Jian Y Gas turbine driven electric power system with constant output through a full range of ambient conditions
US8727697B2 (en) * 2010-03-27 2014-05-20 Rolls-Royce Corporation Variable vane actuation system and method
US20120134783A1 (en) 2010-11-30 2012-05-31 General Electric Company System and method for operating a compressor
US8909454B2 (en) * 2011-04-08 2014-12-09 General Electric Company Control of compression system with independently actuated inlet guide and/or stator vanes
US9068470B2 (en) * 2011-04-21 2015-06-30 General Electric Company Independently-controlled gas turbine inlet guide vanes and variable stator vanes
US10167783B2 (en) 2012-03-09 2019-01-01 United Technologies Corporation Low pressure compressor variable vane control for two-spool turbofan or turboprop engine
US20130287550A1 (en) * 2012-04-25 2013-10-31 General Electric Company Compressor of a gas turbine system
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
GB201221095D0 (en) 2012-11-23 2013-01-09 Rolls Royce Plc Monitoring and control system
US9777641B2 (en) * 2012-12-19 2017-10-03 General Electric Company System for turbomachine vane control
WO2014130628A1 (en) * 2013-02-20 2014-08-28 Carrier Corporation Inlet guide vane mechanism
US9840934B2 (en) * 2013-12-11 2017-12-12 United Technologies Corporation Aero-actuated vanes
FR3031772B1 (en) * 2015-01-19 2017-01-13 Snecma VARIABLE TIMING AUB CONTROL SYSTEM FOR TURBOMACHINE
US10634000B2 (en) 2017-06-23 2020-04-28 Rolls-Royce North American Technologies Inc. Method and configuration for improved variable vane positioning
US20190061918A1 (en) * 2017-08-22 2019-02-28 Hamilton Sundstrand Corporation Electric hydraulic actuation system for a safety critical application
JP7017446B2 (en) * 2018-03-20 2022-02-08 本田技研工業株式会社 Axial flow compressor
US20200024982A1 (en) * 2018-07-18 2020-01-23 United Technologies Corporation Boundary layer ingesting fan
US11560810B1 (en) 2021-07-20 2023-01-24 Rolls-Royce North American Technologies Inc. Variable vane actuation system and method for gas turbine engine performance management

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3502260A (en) * 1967-09-22 1970-03-24 Gen Electric Stator vane linkage for axial flow compressors
GB2078865A (en) * 1980-06-28 1982-01-13 Rolls Royce A variable stator vane operating mechanism for a gas turbine engine
GB2187237A (en) * 1986-02-28 1987-09-03 Mtu Muenchen Gmbh Independently adjustable vanes of a tandem guide vane array in a turbocompressor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2613029A (en) * 1947-06-04 1952-10-07 Rolls Royce Axial flow compressor regulation
US2929546A (en) * 1955-01-26 1960-03-22 Gen Electric Positioning device
US3377799A (en) * 1966-01-03 1968-04-16 Gen Electric Mechanical integrators and control systems employing same
US3685920A (en) * 1971-02-01 1972-08-22 Gen Electric Actuation ring for variable geometry compressors or gas turbine engines
GB1511723A (en) * 1975-05-01 1978-05-24 Rolls Royce Variable stator vane actuating mechanism
DE2740904A1 (en) * 1977-09-10 1979-03-22 Motoren Turbinen Union DEVICE FOR OPERATING SHUT-OFF ELEMENTS IN GAS TURBINE ENGINES, IN PARTICULAR GAS TURBINE JET
JPS5859400A (en) * 1981-10-02 1983-04-08 Hitachi Ltd Apparatus for varying setting angle of stator blades of multi-stage axial-flow compressor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3502260A (en) * 1967-09-22 1970-03-24 Gen Electric Stator vane linkage for axial flow compressors
GB2078865A (en) * 1980-06-28 1982-01-13 Rolls Royce A variable stator vane operating mechanism for a gas turbine engine
GB2187237A (en) * 1986-02-28 1987-09-03 Mtu Muenchen Gmbh Independently adjustable vanes of a tandem guide vane array in a turbocompressor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2410530A (en) * 2004-01-27 2005-08-03 Rolls Royce Plc Electrically actuated stator vane arrangement
EP2557276A3 (en) * 2011-08-08 2017-04-05 General Electric Company Variable stator vane control system
CN110792621A (en) * 2019-11-08 2020-02-14 江苏科技大学 Double-shaft motor fan assembly structure convenient for heat dissipation
CN110792621B (en) * 2019-11-08 2020-10-02 泰安市泰和电力设备有限公司 Double-shaft motor fan assembly structure convenient for heat dissipation
RU2815592C1 (en) * 2023-10-25 2024-03-19 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Axial multistage compressor guide vanes turning mechanism

Also Published As

Publication number Publication date
US5044879A (en) 1991-09-03
GB8901569D0 (en) 1989-03-15
GB2227527B (en) 1993-06-09

Similar Documents

Publication Publication Date Title
US5044879A (en) Variable stator vane arrangement for an axial flow compressor
US3458118A (en) Low profile stator adjusting mechanism
US4812106A (en) Variable stator vane arrangement for a compressor
US4968217A (en) Variable pitch arrangement for a gas turbine engine
US3861822A (en) Duct with vanes having selectively variable pitch
US20210102552A1 (en) Axi-centrifugal compressor with variable outlet guide vanes
US11448127B2 (en) Translating inlet for adjusting airflow distortion in gas turbine engine
US4755104A (en) Stator vane linkage
US4978280A (en) Variable guide vane arrangement for a compressor
US4773817A (en) Labyrinth seal adjustment device for incorporation in a turbomachine
JPS5810600B2 (en) Axial compressor casing
EP0041712B1 (en) Turbo compressor having a surge suppressing arrangement
GB2271393A (en) Adjusting clearance between flow straighteners and a compressor rotor.
EP3473815A1 (en) A variable vane actuation arrangement
US4874287A (en) Variable-geometry turbocompressor
GB2549912A (en) Device for the individual adjustment of a plurality of variable-pitch radial stator vanes in a turbomachine
KR880014227A (en) Partial arc high pressure steam turbine
DE69402372T2 (en) Inlet guide vane against whistling
US11092167B2 (en) Variable vane actuating system
US4640091A (en) Apparatus for improving acceleration in a multi-shaft gas turbine engine
US10794272B2 (en) Axial and centrifugal compressor
US3841790A (en) Compressor flow fence
RU2555928C2 (en) Jet turbine engine
EP0150729A2 (en) Method and apparatus for improving acceleration in a multi-shaft gas turbine engine
RU2555933C2 (en) Gas-turbine engine

Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20020125