GB1064330A - Vane operating mechanism for a fluid flow machine such as a gas turbine engine - Google Patents

Vane operating mechanism for a fluid flow machine such as a gas turbine engine

Info

Publication number
GB1064330A
GB1064330A GB1134/66A GB113466A GB1064330A GB 1064330 A GB1064330 A GB 1064330A GB 1134/66 A GB1134/66 A GB 1134/66A GB 113466 A GB113466 A GB 113466A GB 1064330 A GB1064330 A GB 1064330A
Authority
GB
United Kingdom
Prior art keywords
rings
levers
ball portions
gas turbine
portions
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
GB1134/66A
Inventor
Douglas Herbert Williamson
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 GB1134/66A priority Critical patent/GB1064330A/en
Priority to US602932A priority patent/US3360240A/en
Priority to FR89903A priority patent/FR1507449A/en
Publication of GB1064330A publication Critical patent/GB1064330A/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)

Abstract

1,064,330. Axial flow compressors. ROLLS-ROYCE Ltd. Jan.10, 1966, No.1134/66. Heading F1C. The pivotally mounted stator blades in the high pressure axial flow compressor of a gas turbine by-pass engine are angularly adjustable by axially spaced rings 33, 34 surrounding the compressor casing (15) Fig. 1 (not shown), and engaging ball portions 31 at the opposite ends of levers 27 each attached to the spindle (21) of a blade (20), Fig. 3 (not shown). The rings 33, 34 are rotatable in opposite directions by a pair of rams 35 and thus apply couples to levers 27 to effect rotation of the blades. Springs 40 urge the rings 33, 34 into engagement with the ball portions 31 and may assist in urging the rings towards predetermined relative angular positions. The recesses 32 in the rings engaging ball portions 31 are hemi-spherical and in a modification, Fig. 5 (not shown) the hemispheres are cut away (at 43) to assist assembly of the ball portions therein. The levers 27 have thin portions (30) to accommodate flexing during operation.
GB1134/66A 1966-01-10 1966-01-10 Vane operating mechanism for a fluid flow machine such as a gas turbine engine Expired GB1064330A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB1134/66A GB1064330A (en) 1966-01-10 1966-01-10 Vane operating mechanism for a fluid flow machine such as a gas turbine engine
US602932A US3360240A (en) 1966-01-10 1966-12-19 Vane operating mechanism
FR89903A FR1507449A (en) 1966-01-10 1967-01-04 Blade drive mechanism applicable to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1134/66A GB1064330A (en) 1966-01-10 1966-01-10 Vane operating mechanism for a fluid flow machine such as a gas turbine engine

Publications (1)

Publication Number Publication Date
GB1064330A true GB1064330A (en) 1967-04-05

Family

ID=9716762

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1134/66A Expired GB1064330A (en) 1966-01-10 1966-01-10 Vane operating mechanism for a fluid flow machine such as a gas turbine engine

Country Status (3)

Country Link
US (1) US3360240A (en)
FR (1) FR1507449A (en)
GB (1) GB1064330A (en)

Families Citing this family (6)

* 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
US3873230A (en) * 1974-04-10 1975-03-25 United Aircraft Corp Stator vane actuating mechanism
US4403912A (en) * 1981-03-23 1983-09-13 Avco Corporation Integrated multiplane actuator system for compressor variable vanes and air bleed valve
EP2261466A1 (en) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Adjustment device for stator vanes of a turbine
WO2014189568A2 (en) * 2013-03-13 2014-11-27 United Technologies Corporation Variable vane drive system
US9982686B2 (en) * 2015-11-04 2018-05-29 General Electric Company Turnbuckle dampening links

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2455251A (en) * 1945-10-16 1948-11-30 United Aircraft Corp Constant thrust fan
DE1136350B (en) * 1959-08-11 1962-09-13 Entwicklungsbau Pirna Veb Adjusting device for guide vane rims of an axial flow machine

Also Published As

Publication number Publication date
US3360240A (en) 1967-12-26
FR1507449A (en) 1967-12-29

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