| CPC F02K 1/66 (2013.01) [F02K 1/32 (2013.01)] | 8 Claims |
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1. A turbofan engine comprising: a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel;
a nacelle assembly disposed circumferentially around the variable pitch fan relative to the axis and defining at least in part a bypass passage, a forward opening of the bypass passage, and an aft opening of the bypass passage, the nacelle assembly further defining, in the reverse thrust mode, an intermediate opening disposed aft of the variable pitch fan;
a flow guide assembly including one or more flow channels contained inside an internal portion of the nacelle assembly, wherein the flow guide assembly includes a first aft intermediate flow channel with a first exit portion providing flow outside of an aft section of the nacelle assembly that is aft of the intermediate opening and a second aft intermediate flow channel with a second exit portion providing flow that is aft of the intermediate opening into the bypass passage, the flow guide assembly configured to:
guide a first fluid flow opposite the direction of travel within the bypass passage from the forward opening to the aft opening in the forward thrust mode;
and redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in the reverse thrust mode; and wherein the first aft intermediate flow channel and the second aft intermediate flow channel of the flow guide assembly assist in redirecting the second fluid flow through the intermediate opening; and
a core including one or more core flow channels for generating at least one fluidic injection pressurized by the core, including to the first aft intermediate flow channel and the second aft intermediate flow channel.
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