US3376018A - Vane operating mechanism - Google Patents

Vane operating mechanism Download PDF

Info

Publication number
US3376018A
US3376018A US603652A US60365266A US3376018A US 3376018 A US3376018 A US 3376018A US 603652 A US603652 A US 603652A US 60365266 A US60365266 A US 60365266A US 3376018 A US3376018 A US 3376018A
Authority
US
United States
Prior art keywords
arm
operating mechanism
aperture
ring
vanes
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
US603652A
Other languages
English (en)
Inventor
Williamson Douglas Herbert
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
Application granted granted Critical
Publication of US3376018A publication Critical patent/US3376018A/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

Definitions

  • VANE OPERATING MECHANISM Filed Dec. 21, 1966 5 Sheets-Sheet 5 wL-a"
  • a ttorney 3 Unitid States Patent 3,376,018 VANE OPERATING MECHANISM Douglas Herbert Williamson, Derby, England, assiguor to Rolls-Royce Limited, Derby, England, a British company Filed Dec. 21, 1966, Ser. No. 603,652 Claims priority, application Great Britain, Jan. 10, 1966,
  • a vane operating mechanism having a rotatable ring, connected by arms to a spindle extending from each vane root, rotation of the ring eifecting pivotal movement of the vane.
  • One end of each arm is part-spherical and is received by an aperture in the ring, the aperture being so shaped that the arm may be introduced into theaperture, and then turned to lock it in position.
  • Each arm has a flexible portion to accommodate deformation during operation.
  • This invention concerns avane operating mechanism and, although the invention is not so restricted, it is more particularly concerned with a mechanism for operating variable stator vanes of a gas turbine engine.
  • vanes as used in this specification is to be understood as including blades.
  • a vane operating mechanism comprising at least one ring, means for rotating the or each ring about its axis and through a predetermined angular range, the or each said ring having associated therewith and being axially spaced from a plurality of angularly spaced apart vanes which are arranged about the said axis and each of which has a radially extending spindle rotation of which effects pivotal movement of the respective vane, and an arm connecting each spindle to its ring so that rotation of the latter eiTects pivotal movement of the vanes associated therewith, each arm having a portion which is located in an aperture in its ring and/ or in its spindle, each said portion and aperture being so formed that the portion may be relatively orientated to introduce it into the aperture and then relatively moved within the aperture to lock it in position therein.
  • Each arm preferably has a flexible part to accommodate the bending to which it is subjected in operation.
  • each said .fiexible part may be a centrally located and relatively thin part of its arm.
  • each arm is preferably part-spherical and is located in a part-spherical aperture, each said portion having been originally introduced into at least one part of the aperture which is non-spherical.
  • each part-spherical aperture may have two diametrically oppositely disposed straight sided enlarged parts, the said portion of each arm having parallel fiat sides for reception within the said enlarged parts.
  • each said aperture is preferably provided in the or a ring, each arm being provided with the said portion at one end thereof and being detachably connected to its spindle at its other end.
  • the said other end of each arm maybe provided with a threaded spigot which is located freely in a hole in the respective spindle, the spigot having a nut threaded thereon by means of which the arm is bolted to the spindle.
  • the means for rotating the or each ring may comprise at least one ram which acts directly upon the respective ring or is connected thereto by an operating linkage.
  • the invention also comprises a gas turbine engine provided with a vane operating mechanism as set forth above.
  • the said vanes may be variable stator vanes of a compressor of the engine.
  • FIGURE 1 is a view, partly in section, of part of a gas turbine engine provided with a vane operating mechanism in accordance with the present invention
  • FIGURE 2 is a broken-away sectional view showing part of the structure of FIGURE 1 on a larger scale
  • FIGURE 3 is a broken-away plan view looking in the direction of the arrow 3 of FIGURE 2,
  • FIGURE 4 is a broken-away sectional. view showing part of the structure of FIGURE 2 on a yet larger scale
  • FIGURE 5 is a broken-away sectional view taken on the line 55 of FIGURE 4, and
  • FIGURE 6 is a broken-away sectional view taken on the line 6-6 of FIGURE 5.
  • a gas turbine by-pass engine 10 has an engine casing 11 within which there are mounted in flow series a low pressure compressor 12, a high pressure compressor 13, combustion equipment (not shown) and high pressure and low pressure turbines (not shown).
  • Part of the air compressed by the low pressure compressor 12 passes to a by-pass passage 14, the by-pass passage 14 being disposed between the engine casing 11 and a casing 15 which forms the outer casing of the high pressure compressor 13.
  • the casing 15 is mounted concentrically within the engine casing 11 and is supported therefrom by way of a plurality of angularly spaced apart struts 16.
  • the high pressure compressor 13 has angularly spaced apart variable stator vanes which are arranged about the engine axis, the vanes 20 being arranged in three axially spaced apart rows.
  • Each of the vanes 20 has radially extending spindles 19, 21, rotation of the spindle 21 effecting pivotal movement of the respective vane 20.
  • Each of the sets of vanes 20 has a ring 22 associated with it and disposed axially upstream of it.
  • Each of the rings 22 is mounted concentrically about the engine axis and is rotatable about this axis through a predetermined angular range.
  • rings 22 are shown disposed axially upstream of the vanes 20, and this is the preferred construction, in some cases the rings 22 could well be disposed downstream of the respective row of vanes 20.
  • the rotation of the rings 22 is eifected by means of at least one ram 23 (FIGURE 3) which is arranged to move the outer end of an arm 24 of a pivotally mounted bell crank lever 24, 25.
  • the .arm 25 of the bell crank lever 24, 25 is pivotally connected to the most downstream of the rings 22, while the arm 24 is connected to the remaining rings 22 by way of bell crank levers 26, 27 respectively.
  • operation of the ram 23 will move the arm 24 through a small angle and will therefore move the rings 22 through a small angle.
  • Each of the spindles 21 is connected to its respective ring 22 by means of a substantially axially extending arm 30.
  • Each of the arms 30 has a centrally located and relatively thin part 31 (best seen in FIGURE 4), which is flexible so as to accommodate the bending to which the arm 30 is subjected in operation.
  • each of the arms 30 is provided both with a flange 32, which is located against the respective spindle 21, and with a spigot 33 which is located freely in a hole 34 in the respective spindle 21.
  • the downstream end of the spigot. 33 is threaded and has a nut 35 screwed onto it so as to clamp the spindle 21 between the flange 32 and the nut 35.
  • Each of the arms 30 has an enlarged part-spherical portion 36 at its upstream end, the part-spherical portion 36 being provided with parallel flat sides 37.
  • each of the rings 22 is provided with a plurality of angularly spaced apart apertures 40, in each of which is received the part-spherical portion 36 of the respective arm 30.
  • each of the apertures 40 is part-spherical and has two diametrically oppositely disposed straight sided enlarged parts 41.
  • the enlarged parts 41 have spaced sides 42 between which the partspherical portion 36 may be passed when the latter is orientated with fiat sides 37 thereof arranged as indicated in dotted lines in FIGURE 5.
  • the part-spherical portion 36 after having been orientated to introduce it into its aperture 40, may then be moved within the aperture through 90 to the full line position shown in FIGURE 5. In this position, which is illustrated in FIGURE 6, the part-spherical portion 36 is locked in the aperture 40.
  • the vane operating mechanism shown in the drawings may be assembled by attaching all the arms 30 to their respective rings 22 by entering the part-spherical portions 36 through the enlarged parts 41 of the apertures 40 and then twisting the arms 30 through 90 so as to effect engagement between the spherical surfaces of the partspherical portion 36 and aperture 40.
  • the assembly of each ring 22 with its arms 30 can then be slid into position so that the spigots 33 enter the corresponding holes 34 in the sprindles 21, and the nuts 35 can then be placed on the threaded portions of the spigots 33 and can be tightened.
  • each of the rings 22 can be inserted in the respective spindles 21 and the nuts 35 can be loosely applied so that the arms 30 can be rotated in the holes 34.
  • the respective ring 22 can then be oifered up to the upstream ends of the arms 30 with all the arms 30 in the positions indicated in dotted lines in FIGURE 5. This enables the part-spherical portions 36 to slide through the enlarged parts 41. All the arms 30 can then be twisted through 90 and the nuts 35 tightened to complete the assembly.
  • variable stator vanes 20 of the high pressure compressor 13 could also of course be used in any compressor, fan or turbine where one or more rows of vanes (or blades) have to be made variable.
  • a vane operating mechanism comprising at least one ring, means for rotating said at least one ring about its axis and through a predetermined angular range, a plurality of angularly spaced-apart vanes, associated with each ring and axially spaced therefrom, said vanes being arranged about the said axis and each having a radially extending spindle rotation of which effects pivotal movement of the respective vane, and an arm connecting each spindle to its respective ring, rotation of the latter effecting pivotal movement of the vanes associated therewith, locking means for connecting and positively retaining each arm to its respective ring, said locking means including providing each arm with an integral portion and providing the respective ring with apertures for receiving the integral portion of the arm, each said integral portion and aperture being formed so that the integral portion may be relatively orientated to introduce it into the aperture by relative movement of the integral portion and the aperture substantially parallel to the axis of the ring and then relatively moved within the aperture to engage sides of the aperture and positively retain the integral portion in the aperture.
  • each arm has a flexible part to accommodate the deformation to which it is subjected in operation.
  • Vane operating mechanism as claimed in claim 2 in which each said flexible part is a centrally located and relatively thin part of its arm.
  • each said aperture has a spherical part and a nonspherical part and the said integral portion of each arm is part-spherical and is positively retained in the spherical part of the aperture, each said portion having been originally introduced into the said non-spherical part of the aperture.
  • Vane operating mechanism as claimed in claim 4 in which the non-spherical part of each aperture comprises two, diametrically oppositely disposed, straight sided enlarged parts, the said integral portion of each arm having parallel flat sides for reception within the said enlarged parts.
  • each arm being provided with the said integral portion at one end thereof and being detachably connected to its spindle at its other end.
  • each spindle has a hole therethrough and the said other end of each arm is provided with a threaded spigot which is located freely in the hole in the respective spindle, the spigot having a nut threaded thereon by means of which the arm is bolted to the spindle.
  • Vane operating mechanism as claimed in claim 1 in which the means for rotating each ring comprises at least one ram operatively connected to the at least ring.
  • a gas turbine engine provided with a vane operating mechanism as claimed in claim 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
US603652A 1966-01-10 1966-12-21 Vane operating mechanism Expired - Lifetime US3376018A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1123/66A GB1063602A (en) 1966-01-10 1966-01-10 Vane operating mechanism for a fluid flow machine

Publications (1)

Publication Number Publication Date
US3376018A true US3376018A (en) 1968-04-02

Family

ID=9716556

Family Applications (1)

Application Number Title Priority Date Filing Date
US603652A Expired - Lifetime US3376018A (en) 1966-01-10 1966-12-21 Vane operating mechanism

Country Status (4)

Country Link
US (1) US3376018A (fr)
DE (1) DE1601625A1 (fr)
FR (1) FR1507701A (fr)
GB (1) GB1063602A (fr)

Cited By (16)

* 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
US3461685A (en) * 1967-08-02 1969-08-19 Trane Co Inlet guide vane actuating arrangement for multistage centrifugal compressor
US3487992A (en) * 1967-11-01 1970-01-06 Gen Electric Stator adjusting mechanism for axial flow compressors
US3566916A (en) * 1969-05-01 1971-03-02 Ruskin Mfg Co Inlet vane damper
FR2582729A1 (fr) * 1985-06-03 1986-12-05 Gen Electric Levier de manoeuvre pour aubes de stators variables
US4990056A (en) * 1989-11-16 1991-02-05 General Motors Corporation Stator vane stage in axial flow compressor
US6471471B1 (en) * 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US20020182064A1 (en) * 2001-05-11 2002-12-05 Fiatvio S.P.A. Axial turbine for aeronautical applications
US6682299B2 (en) 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
US6779971B2 (en) * 2000-10-12 2004-08-24 Holset Engineering Company, Limited Turbine
FR2879685A1 (fr) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine a stator comprenant un etage d'aubes de redresseur a calage variable avec reglage de jeu au niveau du pivot d'aube
FR2879684A1 (fr) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine comprenant un stator equipe d'aubes de redresseur a calage variable commandees par des biellettes a emmanchement conique
FR2879688A1 (fr) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine a stator comportant un etage d'aubes de redresseur a calage variable avec reglage de jeu au voisinage des pivots des aubes
WO2012013909A1 (fr) * 2010-07-30 2012-02-02 Turbomeca Dispositif de commande d'aubes pivotantes de turbomachine
RU2511880C2 (ru) * 2012-08-24 2014-04-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Устройство для регулировки угла поворота лопаток направляющего аппарата компрессора
US20230061349A1 (en) * 2021-08-25 2023-03-02 Rolls-Royce Corporation Variable outlet guide vanes

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4279568A (en) * 1978-10-16 1981-07-21 United Technologies Corporation Vane angle control
FR2739137B1 (fr) * 1995-09-27 1997-10-31 Snecma Dispositif de commande d'un etage d'aubes a calage variable

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1096708A (fr) * 1953-12-30 1955-06-23 Hispano Suiza Sa Perfectionnements apportés aux appareils à aubage supersonique, notamment aux compresseurs supersoniques
DE1022348B (de) * 1955-07-26 1958-01-09 Bmw Studiengesellschaft Fuer T Verstellvorrichtung fuer die Leitschaufeln von Stroemungsmaschinen
US2933234A (en) * 1954-12-28 1960-04-19 Gen Electric Compressor stator assembly
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
US2976015A (en) * 1957-04-04 1961-03-21 Napier & Son Ltd Turbine stator blade rings
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
US3303992A (en) * 1965-03-03 1967-02-14 Gen Motors Corp Variable vane stator ring

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1096708A (fr) * 1953-12-30 1955-06-23 Hispano Suiza Sa Perfectionnements apportés aux appareils à aubage supersonique, notamment aux compresseurs supersoniques
US2933234A (en) * 1954-12-28 1960-04-19 Gen Electric Compressor stator assembly
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
DE1022348B (de) * 1955-07-26 1958-01-09 Bmw Studiengesellschaft Fuer T Verstellvorrichtung fuer die Leitschaufeln von Stroemungsmaschinen
US2976015A (en) * 1957-04-04 1961-03-21 Napier & Son Ltd Turbine stator blade rings
US2999630A (en) * 1957-08-08 1961-09-12 Gen Electric Compressor
US3303992A (en) * 1965-03-03 1967-02-14 Gen Motors Corp Variable vane stator ring

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3461685A (en) * 1967-08-02 1969-08-19 Trane Co Inlet guide vane actuating arrangement for multistage centrifugal compressor
US3458118A (en) * 1967-08-21 1969-07-29 Gen Electric Low profile stator adjusting mechanism
US3487992A (en) * 1967-11-01 1970-01-06 Gen Electric Stator adjusting mechanism for axial flow compressors
US3566916A (en) * 1969-05-01 1971-03-02 Ruskin Mfg Co Inlet vane damper
FR2582729A1 (fr) * 1985-06-03 1986-12-05 Gen Electric Levier de manoeuvre pour aubes de stators variables
US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes
US4990056A (en) * 1989-11-16 1991-02-05 General Motors Corporation Stator vane stage in axial flow compressor
US6779971B2 (en) * 2000-10-12 2004-08-24 Holset Engineering Company, Limited Turbine
US6471471B1 (en) * 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US20020182064A1 (en) * 2001-05-11 2002-12-05 Fiatvio S.P.A. Axial turbine for aeronautical applications
US6860717B2 (en) * 2001-05-11 2005-03-01 Avio S.P.A. Axial turbine for aeronautical applications
US6682299B2 (en) 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
FR2879685A1 (fr) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine a stator comprenant un etage d'aubes de redresseur a calage variable avec reglage de jeu au niveau du pivot d'aube
FR2879684A1 (fr) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine comprenant un stator equipe d'aubes de redresseur a calage variable commandees par des biellettes a emmanchement conique
FR2879688A1 (fr) * 2004-12-16 2006-06-23 Snecma Moteurs Sa Turbomachine a stator comportant un etage d'aubes de redresseur a calage variable avec reglage de jeu au voisinage des pivots des aubes
WO2012013909A1 (fr) * 2010-07-30 2012-02-02 Turbomeca Dispositif de commande d'aubes pivotantes de turbomachine
FR2963384A1 (fr) * 2010-07-30 2012-02-03 Turbomeca Dispositif de commande d'aubes pivotantes de turbomachine
CN103189602A (zh) * 2010-07-30 2013-07-03 涡轮梅坎公司 一种控制涡轮机枢转叶片的装置
CN103189602B (zh) * 2010-07-30 2015-12-09 涡轮梅坎公司 一种控制涡轮机枢转叶片的装置
RU2600199C2 (ru) * 2010-07-30 2016-10-20 Турбомека Устройство для управления поворотными лопатками турбомашины и турбомашина, содержащая такое устройство
US9551234B2 (en) 2010-07-30 2017-01-24 Turnomeca Device for controlling pivotable vanes of a turbo-machine
RU2511880C2 (ru) * 2012-08-24 2014-04-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Устройство для регулировки угла поворота лопаток направляющего аппарата компрессора
US20230061349A1 (en) * 2021-08-25 2023-03-02 Rolls-Royce Corporation Variable outlet guide vanes
US11686211B2 (en) * 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet guide vanes

Also Published As

Publication number Publication date
DE1601625A1 (de) 1970-08-06
GB1063602A (en) 1967-03-30
FR1507701A (fr) 1967-12-29

Similar Documents

Publication Publication Date Title
US3376018A (en) Vane operating mechanism
US5024580A (en) Control of variable stator vanes
US4755104A (en) Stator vane linkage
US3123283A (en) Anti-icing valve means
US4430043A (en) Variable stator vane operating mechanism for turbomachines
US3458118A (en) Low profile stator adjusting mechanism
US3861822A (en) Duct with vanes having selectively variable pitch
US4571936A (en) Length adjustable strut link with low aerodynamic drag
EP0598174B1 (fr) Turbosoufflante pour une machine à combustion interne
US20160333729A1 (en) Turbine engine having variable pitch outlet guide vanes
DE3819232C2 (de) Einstellbare Statorschaufelanordnung für einen Axialströmungskompressor
US9869190B2 (en) Variable-pitch rotor with remote counterweights
US2520697A (en) Internal-combustion turbine plant
US6332754B1 (en) Steam turbine
US2858062A (en) Variable stator mechanism
US4767264A (en) Vane lever arm construction
US2842305A (en) Compressor stator assembly
EP2543829A2 (fr) Capteur de gaz
US2955744A (en) Compressor
US20200141265A1 (en) Casing assembly for a gas turbine engine
US3107690A (en) Gas turbine engine having adjustable guide vanes
US10385868B2 (en) Strut assembly for an aircraft engine
US10100653B2 (en) Variable pitch fan blade retention system
US3360240A (en) Vane operating mechanism
US3113430A (en) Gas turbine engine