Ice reduction mechanism for turbofan engine

A 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;
• 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;
• and
• an oil supply assembly in thermal communication with a leading edge of the inlet pre-swirl feature, wherein the oil supply assembly includes an oil supply duct in flow communication with an engine oil and the leading edge of the inlet pre-swirl feature, the oil supply duct configured to receive and provide the engine oil to the leading edge of the inlet pre-swirl feature.