GB1067930A - Vane operating mechanism for fluid flow machines - Google Patents

Vane operating mechanism for fluid flow machines

Info

Publication number
GB1067930A
GB1067930A GB55140/65A GB5514065A GB1067930A GB 1067930 A GB1067930 A GB 1067930A GB 55140/65 A GB55140/65 A GB 55140/65A GB 5514065 A GB5514065 A GB 5514065A GB 1067930 A GB1067930 A GB 1067930A
Authority
GB
United Kingdom
Prior art keywords
vanes
gear teeth
vane
ring
spindle
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
Application number
GB55140/65A
Inventor
James Alexander Petrie
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 GB55140/65A priority Critical patent/GB1067930A/en
Priority to US600914A priority patent/US3352537A/en
Publication of GB1067930A publication Critical patent/GB1067930A/en
Expired legal-status Critical Current

Links

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

Landscapes

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

Abstract

1,067,930. Axial-flow compressors; turbines. ROLLS-ROYCE Ltd. Dec. 29, 1965, No. 55140/65. Headings F1C and F1T. The invention relates to a vane operating mechanism and is described with reference to a variable stator vane assembly of the high pressure compressor of a gas turbine jet engine of the by-pass type. The mechanism comprises a ring formed at one side thereof with gear teeth, means being provided for rotating the ring about its axis through a predetermined angular range, there being a plurality of angularly spaced apart, pivotally mounted vanes which are arranged about the axis and each of which has a radially extending spindle, rotation of which effects pivotal movement of the respective vane, each spindle being provided with gear teeth which are in mesh with the gear teeth on the ring. In the assembly shown each stator vane 21 carries spindles 22, 23 at its radially outer and inner ends respectively the spindles being mounted for rotation in the adjacent stator parts 15, 24. The spindle 23 of each vane is formed with a gear sector 26 which is in mesh with gear teeth 30 formed on a ring member 31 which is rotatable about the engine axis through a predetermined angular range. A roller 43 is carried on the spindle 23 and engages a track 40 in an annular track member 37, the inwardly directed flange 41 of the track member being acted on by an annular spring 44 of sinuous form which also bears against a flange 36 which is connected to the ring member 31. The spring 44 thus serves to maintain the gear teeth 26 and 30 in engagement. Two of the vanes 21 have levers which are acted on by rams 45 Fig. 3 (not shown), rotational movement of these two vanes producing corresponding movement of the other vanes. In a second embodiment the operating mechanism is disposed at the radially outer ends of the vanes and in this case the ring member 31 is acted on directly by the actuating rams.
GB55140/65A 1965-12-29 1965-12-29 Vane operating mechanism for fluid flow machines Expired GB1067930A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB55140/65A GB1067930A (en) 1965-12-29 1965-12-29 Vane operating mechanism for fluid flow machines
US600914A US3352537A (en) 1965-12-29 1966-12-12 Vane operating mechanism for fluid flow machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB55140/65A GB1067930A (en) 1965-12-29 1965-12-29 Vane operating mechanism for fluid flow machines

Publications (1)

Publication Number Publication Date
GB1067930A true GB1067930A (en) 1967-05-10

Family

ID=10473073

Family Applications (1)

Application Number Title Priority Date Filing Date
GB55140/65A Expired GB1067930A (en) 1965-12-29 1965-12-29 Vane operating mechanism for fluid flow machines

Country Status (2)

Country Link
US (1) US3352537A (en)
GB (1) GB1067930A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237072A (en) * 1989-09-06 1991-04-24 Rolls Royce Plc A variable pitch arrangement for a gas turbine engine
GB2301867A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Supporting unison rings in pivotable vane actuating mechanisms

Families Citing this family (20)

* 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
GB1211447A (en) * 1968-09-17 1970-11-04 Leyland Gas Turbines Ltd Turbine having variable angle nozzle guide vanes
US4003675A (en) * 1975-09-02 1977-01-18 Caterpillar Tractor Co. Actuating mechanism for gas turbine engine nozzles
US4239450A (en) * 1979-05-17 1980-12-16 Buffalo Forge Company Adjusting mechanism for variable inlet vane
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US4932206A (en) * 1988-08-17 1990-06-12 Sundstrand Corporation Guide vane assembly for auxiliary power unit
ITTO20010445A1 (en) * 2001-05-11 2002-11-11 Fiatavio Spa STATOR OF A VARIABLE GEOMETRY AXIAL TURBINE FOR AIRCRAFT APPLICATIONS.
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
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
US8240983B2 (en) * 2007-10-22 2012-08-14 United Technologies Corp. Gas turbine engine systems involving gear-driven variable vanes
US20110176913A1 (en) * 2010-01-19 2011-07-21 Stephen Paul Wassynger Non-linear asymmetric variable guide vane schedule
EP3036404B1 (en) * 2013-08-21 2021-05-19 Raytheon Technologies Corporation Variable area turbine arrangement with secondary flow modulation
US11391298B2 (en) 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
US10450890B2 (en) 2017-09-08 2019-10-22 Pratt & Whitney Canada Corp. Variable stator guide vane system
US10808568B2 (en) * 2018-09-12 2020-10-20 Raytheon Technologies Corporation Airfoil assembly for a gas turbine engine
US11346241B2 (en) * 2020-05-28 2022-05-31 Pratt & Whitney Canada Corp. Variable guide vanes assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR586272A (en) * 1923-10-27 1925-03-20 Bbc Brown Boveri & Cie Vibration-free mounting device for mobile diffusers of centrifugal compressors
GB223941A (en) * 1923-10-27 1925-04-23 Aktiengesellschaft Brown, Boveri & Cie.
US2923459A (en) * 1956-01-20 1960-02-02 Thompson Ramo Wooldridge Inc Vane positioning device
US2994509A (en) * 1959-04-10 1961-08-01 Curtiss Wright Corp Variable area turbine nozzle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237072A (en) * 1989-09-06 1991-04-24 Rolls Royce Plc A variable pitch arrangement for a gas turbine engine
GB2237072B (en) * 1989-09-06 1993-12-01 Rolls Royce Plc A variable pitch arrangement for a gas turbine engine
GB2301867A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Supporting unison rings in pivotable vane actuating mechanisms

Also Published As

Publication number Publication date
US3352537A (en) 1967-11-14

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