Dual function cascade integrated variable area fan nozzle and thrust reverser
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United States of America Patent
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Nov 15, 2022
Grant Date -
Oct 15, 2020
app pub date -
Jun 8, 2020
filing date -
Oct 12, 2006
priority date (Note) -
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Abstract
A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.
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