US 2024/0190573 A1 · AIRCRAFT THERMAL ANTI-ICING SYSTEM

Abstract

An aircraft system is provided that includes a propulsor rotor, a powerplant, a cooling system, an anti-icing system and an aircraft structure. The powerplant is operatively and rotatably coupled to the propulsor rotor. The cooling system includes a cooling circuit and an air duct. The cooling circuit is thermally coupled with the powerplant to extract heat energy from the powerplant. The cooling circuit is thermally coupled with air flowing within the air duct to transfer the heat energy into the air and provide heated air. The anti-icing system includes an inlet fluidly coupled with the air duct. The anti-icing system is adapted to bleed some of the heated air from the air duct through the inlet to provide bleed air. The aircraft structure includes an exterior surface. The anti-icing system is adapted to direct the bleed air into the aircraft structure to heat the exterior surface.

Claims20

Dependent claims

An aircraft system, comprising:

a propulsor rotor;
a powerplant operatively and rotatably coupled to the propulsor rotor;
a cooling system including a cooling circuit and an air duct, the cooling circuit thermally coupled with the powerplant to extract heat energy from the powerplant, and the cooling circuit thermally coupled with air flowing within the air duct to transfer the heat energy into the air and provide heated air;
an anti-icing system including an inlet fluidly coupled with the air duct, the anti-icing system adapted to bleed some of the heated air from the air duct through the inlet to provide bleed air;
and
an aircraft structure comprising an exterior surface, the anti-icing system adapted to direct the bleed air into the aircraft structure to heat the exterior surface.

3 more elements

Dependencies are inferred from the claim text.

Aircraft thermal anti-icing system

Life of this patent

Aircraft thermal anti-icing system

Life of this patent

Abstract

Claims20