Dual function cascade integrated variable area fan nozzle and thrust reverser
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United States of America Patent
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Sep 12, 2017
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N/A
app pub date -
Dec 21, 2011
filing date -
Oct 12, 2006
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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 bypass flow defines a bypass ratio greater than about six (6). 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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