Thrust reverser assembly
AssigneeMRA Systems, Inc.
InventorsDavid Patrick Calder, Graham Frank Howarth, Andrew Michael Roach, Timothy Robert Beasman
Life of this patent
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Abstract
A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and a deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.
Claims20
A gas turbine engine, comprising:
- a core engine;
- a nacelle surrounding at least a portion of the core engine;
- a bypass duct defined by and between the nacelle and the core engine and defining a fore-to-aft airflow conduit;
- an outer door movable between a stowed position and a deployed position, where the outer door extends outwards from the nacelle;
- a blocker door extending between a fore end and an aft end and movable between a stowed position and a deployed position, where the blocker door extends into the airflow conduit to deflect airflow outwards;
- and
- a rotary actuator assembly located aft of the fore end of the blocker door and rotatable about a hinge point having an axis extending in a circumferential direction with respect to the core engine, operably coupled to the outer door and transferring a torque to the outer door to rotate the outer door about the hinge point between the stowed and the deployed positions and operably coupled to the blocker door and transferring a torque to the blocker door to rotate the blocker door about the hinge point between the stowed and the deployed positions.
A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine to define a bypass duct between the nacelle and the core engine, the thrust reverser assembly comprising:
- an outer door movable between a stowed position and a deployed position, where the outer door extends outwards from the nacelle;
- a blocker door extending between a fore end and an aft end and movable between a stowed position and a deployed position, where the blocker door extends into an airflow conduit defined by the bypass duct to deflect air outwards;
- and
- a rotary actuator assembly located aft of the fore end of the blocker door and rotatable about a hinge point having an axis extending in a circumferential direction with respect to the core engine, operably coupled to the outer door and transferring a torque to the outer door to rotate the outer door about the hinge point between the stowed and the deployed positions and operably coupled to the blocker door and transferring a torque to the blocker door to rotate the blocker door about the hinge point between the stowed and the deployed positions.
A method of operating a thrust reverser system for an aircraft, the thrust reverser system including an outer door and a blocker door, the method comprising:
- deploying, by a rotary actuator rotatable at a hinge point about an axis extending in a circumferential direction with respect to a core engine of the aircraft and located aft of a fore end of the blocker door, the outer door from a stowed position to a deployed position, where the rotary actuator transfers a torque to rotate the outer door at the hinge point outwards from a nacelle of a gas turbine engine of the aircraft;
- and
- deploying, by the rotary actuator, the blocker door from a stowed position to a deployed position, where the rotary actuator transfers a torque to rotate the blocker door at the hinge point into an airflow conduit defined by a bypass duct defined by and between the nacelle and the core engine;
- wherein the blocker door and the outer door redirect fan duct airflow causing the airflow to exit out and forward as guided by the deployed outer door.
Dependencies are inferred from the claim text.