US 12,168,956 B2
Ice reduction mechanism for turbofan engine
Arthur William Sibbach, Boxford, MA (US); Allan George van de Wall, Cincinnati, OH (US); Sean Christopher Binion, Loveland, OH (US); Brian Lewis Devendorf, Georgetown, MA (US); and Brandon Wayne Miller, Liberty Township, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jul. 17, 2023, as Appl. No. 18/353,472.
Application 18/353,472 is a continuation of application No. 17/408,770, filed on Aug. 23, 2021, granted, now 11,739,689.
Prior Publication US 2024/0003294 A1, Jan. 4, 2024
Int. Cl. F02C 7/047 (2006.01); B64D 33/02 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/047 (2013.01) [B64D 33/02 (2013.01); F02K 3/06 (2013.01); B64D 2033/0233 (2013.01)] 19 Claims
OG exemplary drawing
 
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.