Gas turbine engine with axial movable fan variable area nozzle
US-9822732-B2 · Nov 21, 2017 · US
US8997497B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8997497-B2 |
| Application number | US-91520810-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 29, 2010 |
| Priority date | Oct 29, 2010 |
| Publication date | Apr 7, 2015 |
| Grant date | Apr 7, 2015 |
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A bypass gas turbine engine includes a variable area fan nozzle with a second fan nacelle section axially movable relative to a first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes a leading edge region that defines a concave external contour and the first fan nacelle section includes a trailing edge region that defines a convex internal contour.
Opening claim text (preview).
What is claimed is: 1. A nacelle assembly for a gas turbine engine comprising: a core nacelle defined about an engine centerline axis of rotation; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; a variable area nozzle in communication with said fan bypass flow path, said variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first…
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