CPC F01D 9/041 (2013.01) [F01D 25/24 (2013.01); F05D 2240/12 (2013.01); F05D 2240/14 (2013.01); F05D 2250/51 (2013.01); F05D 2260/14 (2013.01)] | 20 Claims |
1. A turbofan engine defining a longitudinal axis, the turbofan engine comprising:
a fan comprising a plurality of fan blades;
a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath;
a nacelle surrounding and at least partially enclosing the fan, the nacelle including an inlet at a leading edge of the nacelle, the inlet defining an interior inlet surface that is non-annular; and
an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle.
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