Ice reduction mechanism for turbofan engine
A turbofan engine is provided. The turbofan engine includes 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 a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.
1. 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, 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.
2. The turbofan engine of claim 1 , wherein the electrical device comprises an electrical heating element in thermal communication with the inlet pre-swirl feature.
3. The turbofan engine of claim 2 , wherein the electrical heating element is disposed in a leading edge of the inlet pre-swirl feature.
4. The turbofan engine of claim 3 , wherein the electrical heating element comprises a first element adjacent the leading edge of the inlet pre-swirl feature and a second element positioned aft of the first element within the inlet pre-swirl feature.
5. The turbofan engine of claim 2 , wherein the electrical device includes an electrical supply assembly comprising an electrical supply cable in electrical communication with the electrical heating element.
6. The turbofan engine of claim 1 , wherein the electrical device comprises two electrical heating elements in thermal communication with the inlet pre-swirl feature.
7. The turbofan engine of claim 1 , wherein the electrical device comprises four electrical heating elements in thermal communication with the inlet pre-swirl feature.
8. The turbofan engine of claim 1 , wherein the electrical device is disposed within each of the plurality of part span inlet guide vanes.
9. The turbofan engine of claim 1 , further comprising a vibration assembly in communication with the inlet pre-swirl feature.
10. The turbofan engine of claim 1 , further comprising a piezoelectric transducer that vibrates the inlet pre-swirl feature.
11. The turbofan engine of claim 1 , further comprising an anti-ice coating covering the inlet pre-swirl feature, wherein the anti-ice coating has a shore hardness between Shore A50 and Shore D60.
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.
13. The nacelle assembly of claim 12 , wherein the electrical device comprises an electrical heating element in thermal communication with the inlet pre-swirl feature.
14. The nacelle assembly of claim 13 , wherein the electrical heating element is disposed in a leading edge of the inlet pre-swirl feature.
15. The nacelle assembly of claim 14 , further comprising a piezoelectric transducer that vibrates the inlet pre-swirl feature, wherein the piezoelectric transducer is within the each of the plurality of part span inlet guide vanes.
16. The nacelle assembly of claim 14 , wherein the electrical heating element comprises a first element adjacent the leading edge of the inlet pre-swirl feature and a second element positioned aft of the first element within the inlet pre-swirl feature.
17. The nacelle assembly of claim 13 , wherein the electrical device includes an electrical supply assembly comprising an electrical supply cable in electrical communication with the electrical heating element.
18. The nacelle assembly of claim 12 , wherein the electrical device comprises two electrical heating elements in thermal communication with the inlet pre-swirl feature.
19. The nacelle assembly of claim 12 , further comprising a vibration assembly in communication with the inlet pre-swirl feature.