Variable area fan nozzle and thrust reverser
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.
1. 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.
2. The gas turbine engine system as recited in claim 1 , further comprising a frame member supporting the nozzle door, wherein the frame member includes openings there through, each opening having a first end open to the bypass passage and a second end open to a surrounding environment when the nozzle door is in the thrust reverse position.
3. The gas turbine engine system as recited in claim 2 , wherein the nozzle door covers the second end of each opening in the stowed position such that each opening is a blind opening.
4. The gas turbine engine system as recited in claim 3 , wherein a length of each blind opening from the first end to the second end corresponds to an acoustic characteristic of the bypass airflow.
5. The gas turbine engine system as recited in claim 1 , wherein the stowed position corresponds to an aircraft cruise condition, the intermediate position corresponds to an aircraft take-off condition, and the thrust reverse position corresponds to an aircraft condition after landing.
6. The gas turbine engine system as recited in claim 1 , wherein the first end extends in a radially outward direction from the nacelle relative to a centerline axis of the gas turbine engine core and the second end extends in a radial inward direction into the fan bypass passage, in the thrust reverse position.
7. The gas turbine engine system as recited in claim 1 , wherein movement of the nozzle door changes a variable cross-sectional area associated with the fan bypass passage to influence the bypass airflow.
8. The gas turbine engine system as recited in claim 1 , wherein movement of the nozzle door from the stowed position or the intermediate position to the thrust reverse position opens an auxiliary flow passage between the nozzle door and the nacelle to influence the bypass airflow.
9. The nozzle as recited in claim 1 , wherein the actuator is pivotably connected to the linkage.
10. The gas turbine engine system as recited in claim 1 , wherein at least a portion of the nozzle door is configured to move radially outward of the nacelle.