Thrust reverser and variable area fan nozzle actuation system and method
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United States of America Patent
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Mar 17, 2015
Grant Date -
Jun 7, 2012
app pub date -
Dec 3, 2010
filing date -
Dec 3, 2010
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Abstract
There is provided an actuation system for a gas turbine engine including a thrust reverser and a variable area fan nozzle. The system has a plurality of linear actuators each having a first outer piston concentric with a second inner piston. The first outer piston is operatively connected to a thrust reverser. The second inner piston is operatively connected to a variable area fan nozzle. The system further has a piston lock assembly for selectively locking the first outer piston to the second inner piston. The system further has a control system coupled to the plurality of linear actuators for operating the variable area fan nozzle between a stowed position and a deployed position.
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