AIRCRAFT THERMAL ANTI-ICING SYSTEM

An aircraft system (20) is provided that includes a propulser rotor (46), a powerplant (48), a cooling system (50), an anti-icing system (26) and an aircraft structure (22). The powerplant (48) is operatively and rotatably coupled to the propulser rotor (46). The cooling system (50) includes a cooling circuit (98) and an air duct (96). The cooling circuit (98) is thermally coupled with the powerplant (48) to extract heat energy from the powerplant (48). The cooling circuit (98) is thermally coupled with air flowing within the air duct (96) to transfer the heat energy into the air and provide heated air. The anti-icing system (26) includes an inlet (118) fluidly coupled with the air duct (96). The anti-icing system (26) is adapted to bleed some of the heated air from the air duct (96) through the inlet (118) to provide bleed air. The aircraft structure (22) includes an exterior surface (28). The anti-icing system (26) is adapted to direct the bleed air into the aircraft structure (22) to heat the exterior surface (28).