US3685920A - Actuation ring for variable geometry compressors or gas turbine engines - Google Patents

Actuation ring for variable geometry compressors or gas turbine engines Download PDF

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Publication number
US3685920A
US3685920A US111411A US3685920DA US3685920A US 3685920 A US3685920 A US 3685920A US 111411 A US111411 A US 111411A US 3685920D A US3685920D A US 3685920DA US 3685920 A US3685920 A US 3685920A
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United States
Prior art keywords
bridge
sectors
bolt
sector
levers
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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
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US111411A
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English (en)
Inventor
Joseph C Burge
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General Electric Co
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General Electric Co
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Publication date
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Publication of US3685920A publication Critical patent/US3685920A/en
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical

Definitions

  • ABSTRACT An improved actuation ring for controlling the angular position of compressor vanes connected by levers thereto is described. Two arcuate sectors of less than 180 angular extent are joined by bridge members.
  • Each connection between a sector and a bridge member includes a dowel bushing, a bolt extending through the bushing with a loose fit therebetween with a nut threaded onto its inner end and a second bolt extending through the sector and bridge member with a loose fit therebetween and a nut threaded onto its inner end.
  • the present invention relates to axial flow compressors as used in gas turbine engines and, more particularly, to improvements in actuation rings employed in varying the angular position of the vanes of such compressors.
  • Axial flow compressors generally comprise alternate circumferential rows of rotor blades and casingmounted vanes. These blades and vanes are oriented: radially of the rotor axis.
  • the aerodynamic shapes of these blades and vanes are idealized for operation at a given set of parameters representing the most important operating condition of the compressor or gas turbine engine in which it is incorporated. At other operating conditions, such as at a lesser rotor speed, the design point aerodynamics are ineflicient to the point where the compressor may actually stall and no longer pressurize air.
  • the dowel bushing extends through accurately aligned, radial holes in the bridge member and sector with a tight. tit to obtain precise angular positioning.
  • One bolt extends through the dowel bushing with a loose fit permitting it to be readily threaded into or out of a nut on the inner surface of the sector.
  • the other nut extends through aligned, radial holes in the bridge member and sector with a loose fit so that it may also be threaded into a nut on the inner surface of the sector. With the loose fits of the bolts, the nuts may be simply held against rotation as the bolts are turned to clamp or unclamp the assembly.
  • the object of the invention is to provide an improved actuation ring assembly which has accurate angular positioning of its component parts and which permits easy assembly and disassembly while maintaining other requirements, such as minimum weight and small envelope size.
  • an actuation ring assembly comprising at least two sectors, to which vane levers are to be attached. These sectors have an angular extent of less than 180 and are joined by bridge members to form a complete ring. The bridge members overlie and are fastened to adjacent end portions of the sectors. The connection between each bridge member
  • FIG. 1- is a schematic representation of a gas turbine engine in which the present invention is embodied
  • FIG. 2 is a cross-sectional view, on an enlarged scale, of a portion of the compressor casing and actuator ring seen in FIG. 1;
  • FIG. 3 is a section, on a further enlarged scale, taken on line lIlIII in FIG. 2;
  • FIG. 4 isa. smaller scale view of an actuation ring assembly.
  • FIG. 1 is a simplified external view of a gas turbine engine.
  • outer casing 10 there are, in series flow arrangement, a compressor, a combustor' and a turbine which generate a high energy motive fluid stream. A portion of the energy of this motive fluid stream. drives the turbine which, in turn, powers the rotor of the compressor, all in known fashion. The remainder of the energy in the motive fluid stream may be converted'to a propulsive force by being discharged from a nozzle 12. on the opposite side of the casing 10 to balance the forces transmitted into the actuation rings.
  • the compressor of this engine is of the axial flow, multistage type comprising alternate, circumferential rows of rotor blades and stationary stator vanes. Some or all of the rows of the stator vanes are pivotally adjustable about axes radial of the rotor axis. Such adjustment to provide improved compressor performance trolled by known means to pivot the arm 22 and thus vary the angular positions of the adjustable vanes.
  • a similar arm and actuator may be provided ON THE OPPOSITE SIDE OF THE CASING TO BALANCE THE FORCESTRANSMITIED INTO'TI-IE ACTUA- TION RINGS.
  • the referenced actuation system is described in greater detail in US. Pat. No. 3,314,595. Also, it isto-be noted that other mechanisms are available for rotating such actuation rings.
  • FIGS. 2, 3 and:4 illustrate the present invention.
  • the compressor portion of the casing comprises two semicylindrical shells 28 which have longitudinal flanges 30, joined by bolts 32.
  • Each actuation ring comprises two sectors34 of hollow, square cross section and an angular extent of somewhat less than 180.
  • Each pair of sectors is joined by bridges 36 to which the links are pivotally attached at 38.
  • Each end of each sector 34 is respectively connected to each of the bridges 36 by bolts 40 and 42.
  • Each bolt 40 extends through a hole in the bridge 36, through a tube 44 which is swaged at its opposite ends to the walls of the tubular sector 34 and then is threaded into a nut 46 to clamp the bridge firmly to the sector 34.
  • Each bolt 42 extends through a dowel bushing 48.
  • the dowel bushing (FIG. 3) extends through a hole in the bridge 36 and through a tube 50, also swaged, at its'opposite ends to the sector 34.
  • the dowel bushing has a flanged head 52 at its outer end and terminates short of the inner end of the tube 50.
  • a nut 54 is threaded onto the bolt 42 and also firmly clamps the bridge to the sector 34.
  • a loose fit is provided between the body of the bolt 42 and the dowel bushing'48 so that this bolt may tion as the bolt is torqued for firm clamping action. 7
  • a matched assembly may be prepared by positioning the sectors and bridges on a fixture and line-reaming the holes for the dowel bushings.
  • the dowel bushing 48 and bolts 42 would preferably be first assembled and the nuts 54 tightened by rotation of the bolts 42.
  • the bolts 40 would then be inserted and threaded into the nuts 46. All of the bolts 40 and 42 turn freely so that as sembly is greatly facilitated by simply holding the nuts 46 and 54 against rotation in the crowded work area of the exterior of the compressor casing.
  • FIGS. 2 and 3 show vane levers 16 secured to the actuation ring.
  • the levers 16 may be attached, as taught in US. Pat. No. 3,502,260 of common assignment with the present application.
  • This connection comprises a spherical journal 58 secured to the sectors 34 by bolts 60.
  • the vanes of the compressor are vsoclosely spaced that they must also connect with the bridges 36.
  • spherical journals 58 are secured thereto by shorter bolts 62 ,for other levers 16 to conv of th avmg nect therewith.
  • the bridge 36 preferably has inner legs 64 embracing the end portions of the sectors 34 and an outwardly projecting flange 66 on the side opposite that to which the levers extend. Further, the base portion 68, which engages the .outer surfaces of the sectors 34, has an intermediate portion with an outer surface formed on the same radius as the outer surfaces of the sectors 34.
  • an actuation ring to which the outer ends of the levers are connected, said actuation ring comprising at least two sectors ofless than angular extent bridge members interconnecting said sectors to form a 3609 structure encircling the casing, said bridge members spanning and overlying, respec tively, adjacent end portions of said sectors;
  • each overlying bridge portion being secured to and positioned relative to the respective end portion of thesector by a dowel bushing pro' g radially through said bridge member and sector with a tight fit therebetween to accurately position said bridge member and sector in an angular sense
  • first bolt extending through said bushing with a loose fit a first nut threaded onto the inner end of said first bolt a second bolt, angularly 0am from the first bolt and extending through aligned radial holes in said bridge member and sector witha loose fit and a second nut threaded onto the inner end of said second bolt.
  • portions of the bridge members, intermediatethe sectors, have outer surfaces formed on the same radius as the outer surfaces of the sectors and vane levers are connected to these intermediate bridge portions.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US111411A 1971-02-01 1971-02-01 Actuation ring for variable geometry compressors or gas turbine engines Expired - Lifetime US3685920A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11141171A 1971-02-01 1971-02-01

Publications (1)

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US3685920A true US3685920A (en) 1972-08-22

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Application Number Title Priority Date Filing Date
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Country Status (4)

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US (1) US3685920A (https=)
DE (1) DE2203933A1 (https=)
FR (1) FR2125012A5 (https=)
GB (1) GB1368353A (https=)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3893784A (en) * 1972-11-08 1975-07-08 Bbc Sulzer Turbomaschinen Apparatus for adjusting stator blades
DE2618727A1 (de) * 1975-05-01 1976-11-11 Rolls Royce 1971 Ltd Einrichtung zur verstellung des schaufelanstellwinkels eines verdichterleitschaufelkranzes einer turbomaschine
US4050844A (en) * 1976-06-01 1977-09-27 United Technologies Corporation Connection between vane arm and unison ring in variable area stator ring
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor
US5700129A (en) * 1995-05-04 1997-12-23 Deutsche Forschungsanstalt Fuer Luft- Und Raumfahrt E.V. Temperature-adjustable compressor guide vane ring
EP0909880A3 (en) * 1997-10-14 2000-02-23 General Electric Company Turbine vane actuation system
US20040208742A1 (en) * 2003-04-16 2004-10-21 Snecma Moteurs Device for controlling variable-pitch vanes in a turbomachine
GB2412946A (en) * 2004-04-06 2005-10-12 Rolls Royce Plc A unison ring
US20070020092A1 (en) * 2005-07-20 2007-01-25 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US20070020094A1 (en) * 2005-07-20 2007-01-25 United Technologies Corporation Inner diameter variable vane actuation mechanism
US20070020093A1 (en) * 2005-07-20 2007-01-25 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
FR2922257A1 (fr) * 2007-10-12 2009-04-17 Snecma Sa Perfectionnement a un anneau de commande de calage des aubes fixes d'une turbomachine
US20090285673A1 (en) * 2005-07-20 2009-11-19 United Technologies Corporation Inner diameter vane shroud system having enclosed synchronizing mechanism
US20100115955A1 (en) * 2008-11-11 2010-05-13 Delavan Inc. Thermal management for fuel injectors
RU2454548C2 (ru) * 2006-06-16 2012-06-27 Снекма Статор турбинной установки, содержащий ступень выходных направляющих лопаток, приводимых в движение посредством ротационного венца с автоматической центровкой, компрессор, содержащий вышеуказанный статор, и турбинная установка
US20120195751A1 (en) * 2011-02-01 2012-08-02 Gasmen Eugene C 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
US20160003073A1 (en) * 2014-07-07 2016-01-07 Techspace Aero S.A. Guide vane assembly vane box of an axial turbine engine compressor
US9644491B2 (en) 2014-06-13 2017-05-09 Pratt & Whitney Canada Corp. Single bolting flange arrangement for variable guide vane connection
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
US10634000B2 (en) 2017-06-23 2020-04-28 Rolls-Royce North American Technologies Inc. Method and configuration for improved variable vane positioning
US10724543B2 (en) 2017-08-11 2020-07-28 Raytheon Technologies Corporation Bridge bracket for variable-pitch vane system

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2595117B1 (fr) * 1986-02-28 1991-05-17 Mtu Muenchen Gmbh Turbocompresseur a geometrie variable

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146585A (en) * 1961-09-29 1964-09-01 Gen Electric Turbojet control system for preventing compressor stall due to inlet air disturbances
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
US3314595A (en) * 1965-06-09 1967-04-18 Gen Electric Adjustment mechanism for axial flow compressors
US3325087A (en) * 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines
US3458118A (en) * 1967-08-21 1969-07-29 Gen Electric Low profile stator adjusting mechanism
US3496628A (en) * 1965-04-28 1970-02-24 Usa Method of joining thin-walled members,particularly in casings for gas turbine engines
US3502260A (en) * 1967-09-22 1970-03-24 Gen Electric Stator vane linkage for axial flow compressors

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146585A (en) * 1961-09-29 1964-09-01 Gen Electric Turbojet control system for preventing compressor stall due to inlet air disturbances
US3325087A (en) * 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines
US3496628A (en) * 1965-04-28 1970-02-24 Usa Method of joining thin-walled members,particularly in casings for gas turbine engines
US3314595A (en) * 1965-06-09 1967-04-18 Gen Electric Adjustment mechanism for axial flow compressors
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
US3458118A (en) * 1967-08-21 1969-07-29 Gen Electric Low profile stator adjusting mechanism
US3502260A (en) * 1967-09-22 1970-03-24 Gen Electric Stator vane linkage for axial flow compressors

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3893784A (en) * 1972-11-08 1975-07-08 Bbc Sulzer Turbomaschinen Apparatus for adjusting stator blades
DE2618727A1 (de) * 1975-05-01 1976-11-11 Rolls Royce 1971 Ltd Einrichtung zur verstellung des schaufelanstellwinkels eines verdichterleitschaufelkranzes einer turbomaschine
US4049360A (en) * 1975-05-01 1977-09-20 Rolls-Royce (1971) Limited Variable stator vane actuating mechanism
US4050844A (en) * 1976-06-01 1977-09-27 United Technologies Corporation Connection between vane arm and unison ring in variable area stator ring
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor
US5700129A (en) * 1995-05-04 1997-12-23 Deutsche Forschungsanstalt Fuer Luft- Und Raumfahrt E.V. Temperature-adjustable compressor guide vane ring
EP0909880A3 (en) * 1997-10-14 2000-02-23 General Electric Company Turbine vane actuation system
RU2312225C2 (ru) * 2003-04-16 2007-12-10 Снекма Мотер Устройство для регулировки угла поворота лопаток в турбомашине
US20040208742A1 (en) * 2003-04-16 2004-10-21 Snecma Moteurs Device for controlling variable-pitch vanes in a turbomachine
US7004723B2 (en) * 2003-04-16 2006-02-28 Snecma Moteurs Device for controlling variable-pitch vanes in a turbomachine
GB2412946A (en) * 2004-04-06 2005-10-12 Rolls Royce Plc A unison ring
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US20070020094A1 (en) * 2005-07-20 2007-01-25 United Technologies Corporation Inner diameter variable vane actuation mechanism
US20070020093A1 (en) * 2005-07-20 2007-01-25 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7901178B2 (en) 2005-07-20 2011-03-08 United Technologies Corporation Inner diameter vane shroud system having enclosed synchronizing mechanism
US20090285673A1 (en) * 2005-07-20 2009-11-19 United Technologies Corporation Inner diameter vane shroud system having enclosed synchronizing mechanism
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US20070020092A1 (en) * 2005-07-20 2007-01-25 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
RU2454548C2 (ru) * 2006-06-16 2012-06-27 Снекма Статор турбинной установки, содержащий ступень выходных направляющих лопаток, приводимых в движение посредством ротационного венца с автоматической центровкой, компрессор, содержащий вышеуказанный статор, и турбинная установка
US20090116954A1 (en) * 2007-10-12 2009-05-07 Snecma Pitch control ring for stator vanes of a turbomachine
RU2503823C2 (ru) * 2007-10-12 2014-01-10 Снекма Усовершенствование кольца управления углом установки неподвижных лопаток турбомашины
EP2053203A1 (fr) * 2007-10-12 2009-04-29 Snecma Perfectionnement à un anneau de commande de calage des aubes fixes d'une turbomachine.
US8226357B2 (en) * 2007-10-12 2012-07-24 Snecma Pitch control ring for stator vanes of a turbomachine
FR2922257A1 (fr) * 2007-10-12 2009-04-17 Snecma Sa Perfectionnement a un anneau de commande de calage des aubes fixes d'une turbomachine
US20100115955A1 (en) * 2008-11-11 2010-05-13 Delavan Inc. Thermal management for fuel injectors
US8141368B2 (en) 2008-11-11 2012-03-27 Delavan Inc Thermal management for fuel injectors
US8387400B2 (en) 2008-11-11 2013-03-05 Delavan Inc Thermal management for fuel injectors
US20120195751A1 (en) * 2011-02-01 2012-08-02 Gasmen Eugene C Gas turbine engine synchronizing ring bumper
EP2481891A3 (en) * 2011-02-01 2013-12-18 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US8794910B2 (en) * 2011-02-01 2014-08-05 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
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US9644491B2 (en) 2014-06-13 2017-05-09 Pratt & Whitney Canada Corp. Single bolting flange arrangement for variable guide vane connection
US9611747B2 (en) * 2014-07-07 2017-04-04 Safran Aero Boosters Sa Guide vane assembly vane box of an axial turbine engine compressor
US20160003073A1 (en) * 2014-07-07 2016-01-07 Techspace Aero S.A. Guide vane assembly vane box of an axial turbine engine compressor
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
US10634000B2 (en) 2017-06-23 2020-04-28 Rolls-Royce North American Technologies Inc. Method and configuration for improved variable vane positioning
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
US10724543B2 (en) 2017-08-11 2020-07-28 Raytheon Technologies Corporation Bridge bracket for variable-pitch vane system

Also Published As

Publication number Publication date
GB1368353A (en) 1974-09-25
DE2203933A1 (de) 1972-08-17
FR2125012A5 (https=) 1972-09-22

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