CPC F02C 7/047 (2013.01) [B64D 33/02 (2013.01); F02K 3/06 (2013.01); B64D 2033/0233 (2013.01)] | 19 Claims |
12. A nacelle assembly for a turbofan engine, the turbofan engine comprising a fan including a plurality of fan blades, the nacelle assembly configured to circumferentially surround the fan, the nacelle assembly comprising:
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 assembly, wherein the inlet pre-swirl feature is configured as a plurality of part span inlet guide vanes,
an anti-ice coating covering the inlet pre-swirl feature, wherein the plurality of part span inlet guide vanes are formed of a polymer composite with a metal leading edge, wherein the anti-ice coating is applied only to portions aft of the metal leading edge; and
an electrical device in thermal communication with the inlet pre-swirl feature, wherein the electrical device is configured to reduce ice buildup or ice formation on the inlet pre-swirl feature.
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