Dual function cascade integrated variable area fan nozzle and thrust reverser
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United States of America Patent
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Jun 9, 2020
Grant Date -
Dec 14, 2017
app pub date -
Aug 11, 2017
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 fan nacelle that extends circumferentially about a fan, and at least one integrated mechanism coupled to the fan nacelle. The at least one integrated mechanism includes a variable fan nozzle and a thrust reverser, with the thrust reverser and the variable fan nozzle having a common part.
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