GB979092A - Apparatus for positioning a member in response to two variables - Google Patents

Apparatus for positioning a member in response to two variables

Info

Publication number
GB979092A
GB979092A GB1938063A GB1938063A GB979092A GB 979092 A GB979092 A GB 979092A GB 1938063 A GB1938063 A GB 1938063A GB 1938063 A GB1938063 A GB 1938063A GB 979092 A GB979092 A GB 979092A
Authority
GB
United Kingdom
Prior art keywords
lever
engine
valve
fulcrum
bell
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
GB1938063A
Inventor
David Ian Cowie
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 GB1938063A priority Critical patent/GB979092A/en
Publication of GB979092A publication Critical patent/GB979092A/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
    • F01D17/02—Arrangement of sensing elements
    • 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
    • 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
    • F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
    • F01D17/22—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical
    • F01D17/26—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical fluid, e.g. hydraulic

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)

Abstract

979,092. Axial flow compressors; gas turbine plant. ROLLS-ROYCE Ltd. May 15, 1963, No. 19380/63. Headings F1C and FIG. [Also in Division G3] The inlet guide vanes and a bleed valve of the compressor of a gas turbine engine are controlled by a system comprising an electric signal, responsive to ambient temperature, which is fed to an actuator 54 which rotates a shaft 52 to adjust the fulcrum 44 through a worm 51 and lever 46. The lever 46 is bimetallic to compensate for the temperature of the fuel in the housing. The bell-crank 41 has an arm 43 engaged by the fulcrum 44 and an arm 42 fixed to a control valve 67 which is moved by centrifugal weights 64, on a shaft 60 rotated by the engine, to provide a force responsive to the square of the rotational speed of the engine. The valve 67 controls the supply and exhaust of fluid to the opposite side of a piston 80, the movement of which rotates a lever 85 and through links and linkage 90, 91, 92 causes rotation of a cam 93 to adjust the force of a spring 100, through lever 96, which acts on the bell-crank 41 through lever 103. The lever 85 adjusts the inlet guide vanes and bleed valve (not shown) of the compressor through rods 108, 112 and cranks 111, 116.
GB1938063A 1963-05-15 1963-05-15 Apparatus for positioning a member in response to two variables Expired GB979092A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1938063A GB979092A (en) 1963-05-15 1963-05-15 Apparatus for positioning a member in response to two variables

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1938063A GB979092A (en) 1963-05-15 1963-05-15 Apparatus for positioning a member in response to two variables

Publications (1)

Publication Number Publication Date
GB979092A true GB979092A (en) 1965-01-01

Family

ID=10128393

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1938063A Expired GB979092A (en) 1963-05-15 1963-05-15 Apparatus for positioning a member in response to two variables

Country Status (1)

Country Link
GB (1) GB979092A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2931522A1 (en) * 2008-05-26 2009-11-27 Snecma Linear actuator for e.g. variable bleed valve, of jet engine of airplane or aircraft, has pivot actuator displacing movable pivot with respect to lever according to received set point so that intensity of actuating force is varied

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2931522A1 (en) * 2008-05-26 2009-11-27 Snecma Linear actuator for e.g. variable bleed valve, of jet engine of airplane or aircraft, has pivot actuator displacing movable pivot with respect to lever according to received set point so that intensity of actuating force is varied

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