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US 8,127,529 B2Granted
Variable area fan nozzle and thrust reverser
AssigneeUnited Technologies Corporation
InventorsEdward B. Pero, Leonard D. Aceto
Life of this patent
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Abstract
A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a pivot between the first end and the second end. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage to in turn move the nozzle door about the pivot between a plurality of positions, such as a stowed position, an intermediate position, and a thrust reverse position, to influence a bypass airflow through a fan bypass passage.
Claims10
A gas turbine engine system comprising:
- a fan;
- a nacelle arranged about the fan;
- a gas turbine engine core having a compressor and a turbine at least partially within the nacelle;
- a fan bypass passage downstream of the fan for conveying a bypass airflow, between the nacelle and the gas turbine engine core;
- a nozzle door associated with the fan bypass passage that moves between a stowed position, an intermediate position, and a thrust reverse position to influence the bypass airflow, the nozzle door having a first end, a second end opposed from the first end, and a first pivot between the first end and the second end;
- a linkage connected with the nozzle door;
- an actuator coupled with the linkage, wherein the actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions to influence the bypass airflow through the fan bypass passage;
- a controller that selectively commands the actuator to move the nozzle door;
- and
- a frame member supporting the nozzle door, wherein the frame is pivotally secured to an aftmost end of the nacelle relative to the bypass airflow.
7 more elements
Dependencies are inferred from the claim text.