GB1105926A - Improvements in systems for controlling windmilling of gas turbine engines of multi-engined aircraft - Google Patents

Improvements in systems for controlling windmilling of gas turbine engines of multi-engined aircraft

Info

Publication number
GB1105926A
GB1105926A GB2436265A GB2436265A GB1105926A GB 1105926 A GB1105926 A GB 1105926A GB 2436265 A GB2436265 A GB 2436265A GB 2436265 A GB2436265 A GB 2436265A GB 1105926 A GB1105926 A GB 1105926A
Authority
GB
United Kingdom
Prior art keywords
vanes
bracket
engine
roller
pivoted
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
GB2436265A
Inventor
George William Luebering
Norbert Joseph Meyer
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to DE1965G0043828 priority Critical patent/DE1235676B/en
Priority to GB2436265A priority patent/GB1105926A/en
Publication of GB1105926A publication Critical patent/GB1105926A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162Final 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/02Shutting-down responsive to overspeed

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)

Abstract

1,105,926. Latch fastenings; similarly operated fastenings. GENERAL ELECTRIC CO. 9, June, 1965, No. 24362/65. Heading E2A. [Also in Division Fl] A latching mechanism to lock compressor stator vanes of an aircraft gas turbine engine in the fully closed position to prevent windmilling of the engine in the event of shutdown includes an annular vane operating ring 36 movable circumferentially about the engine casing 20 and pivotally connected to individual vanes (24, Fig. 2, not shown) by links (32). A bracket 58 attached to the ring 36 has pivoted thereon a bellcrank 54, one arm 59 of which is pivoted to an actuating rod 45 controlled by an electrically driven mechanical ram (44, Figs. 4, 5, not shown), and the other arm 62 of which carries a roller 63 and a pivoted locking member 65. In the fully open position of the vanes (Fig. 6, not shown), roller 63 and a projection 75 on bracket 58 respectively engage stops 52, 51 on a bracket 48 fixed to the casing 20. In the event of shut down of the engine, the pilot manually applies a signal to actuate rod 45 which rotates ring 36 clockwise to the position shown to close the stator vanes. In so doing bellcrank 54 pivots about point 56, roller 63 rides along cam surface 50 and locking member 65 engages under the action of spring 74 a lip 72 on bracket 48 to lock the vanes in the closed position. The vanes can only be reset to the open position by operation of a switch when the aircraft is on the ground.
GB2436265A 1965-06-09 1965-06-09 Improvements in systems for controlling windmilling of gas turbine engines of multi-engined aircraft Expired GB1105926A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE1965G0043828 DE1235676B (en) 1965-06-09 1965-06-09 Airstream braking control device
GB2436265A GB1105926A (en) 1965-06-09 1965-06-09 Improvements in systems for controlling windmilling of gas turbine engines of multi-engined aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2436265A GB1105926A (en) 1965-06-09 1965-06-09 Improvements in systems for controlling windmilling of gas turbine engines of multi-engined aircraft

Publications (1)

Publication Number Publication Date
GB1105926A true GB1105926A (en) 1968-03-13

Family

ID=10210540

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2436265A Expired GB1105926A (en) 1965-06-09 1965-06-09 Improvements in systems for controlling windmilling of gas turbine engines of multi-engined aircraft

Country Status (1)

Country Link
GB (1) GB1105926A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2274687A (en) * 1993-01-29 1994-08-03 Turbo Propulsores Ind Indicating failure in gas turbine engine variable aerofoil vane mechanism
EP1990506A3 (en) * 2007-05-08 2012-04-25 Pratt & Whitney Canada Corp. Operation of an aircraft engine after emergency shutdown
US10830086B2 (en) 2018-07-18 2020-11-10 Raytheon Technologies Corporation Cam isolation system for gas turbine engine compressor section

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2274687A (en) * 1993-01-29 1994-08-03 Turbo Propulsores Ind Indicating failure in gas turbine engine variable aerofoil vane mechanism
GB2274687B (en) * 1993-01-29 1996-04-03 Turbo Propulsores Ind Gas turbine engine variable aerofoil vane actuation Mechanism
EP1990506A3 (en) * 2007-05-08 2012-04-25 Pratt & Whitney Canada Corp. Operation of an aircraft engine after emergency shutdown
US10830086B2 (en) 2018-07-18 2020-11-10 Raytheon Technologies Corporation Cam isolation system for gas turbine engine compressor section

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