Aircraft thermal anti-icing system
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.
1. An aircraft system, comprising:
an open propulsor rotor;
a powerplant operatively and rotatably coupled to the open propulsor rotor, the powerplant disposed aft of the open 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, the cooling circuit thermally coupled with air flowing within the air duct to transfer the heat energy into the air and provide heated air, and the air duct extending between an airflow inlet and an airflow exhaust;
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 of the anti-icing system to provide bleed air, and the inlet of the anti-icing system disposed between the cooling circuit and the airflow exhaust; 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.
2. The aircraft system of claim 1 , further comprising a fan downstream of the inlet and configured to propel the bleed air into the aircraft structure.
3. The aircraft system of claim 1 , further comprising a louver arranged at the inlet and configured to direct the heated air from the air duct into the inlet.
4. The aircraft system of claim 1 , further comprising:
means for propelling the bleed air into the aircraft structure; and
means for directing the heated air from the air duct into the inlet.
5. The aircraft system of claim 1 , wherein the air duct is outside of the powerplant.
6. The aircraft system of claim 1 , wherein
the aircraft structure is an aircraft wing; and
the exterior surface forms a leading edge of the aircraft wing.
7. The aircraft system of claim 6 , wherein the bleed air is exhausted from the aircraft wing at a tip of the aircraft wing.
8. The aircraft system of claim 6 , wherein the bleed air is exhausted from the aircraft wing at a trailing edge of the aircraft wing.
9. The aircraft system of claim 1 , wherein
the aircraft structure is an aircraft wing; and
the anti-icing system is configured to direct the bleed air along a leading edge of the aircraft wing to heat the exterior surface.
10. The aircraft system of claim 1 , wherein
the aircraft structure comprises a nacelle housing the powerplant; and
an inlet nose lip of the nacelle includes the exterior surface.
11. The aircraft system of claim 1 , wherein
the aircraft structure comprises a nacelle housing the powerplant; and
the anti-icing system is configured to direct the bleed air along an inlet nose lip of the nacelle to heat the exterior surface.
12. The aircraft system of claim 1 , wherein the cooling circuit flows lubricant for the powerplant.
13. The aircraft system of claim 1 , wherein the cooling circuit flows fuel for the powerplant.
14. The aircraft system of claim 1 , wherein the cooling circuit flows a cooling fluid for the powerplant.
15. The aircraft system of claim 1 , wherein the powerplant comprises a thermal engine.
16. The aircraft system of claim 1 , wherein the powerplant comprises an electric motor.
17. An aircraft system, comprising:
an un-ducted propulsor rotor;
a powerplant configured to drive rotation of the un-ducted propulsor rotor, the un-ducted propulsor rotor disposed forward of the powerplant;
a cooling system including a cooling circuit and an air duct, the cooling circuit configured to transfer heat energy from the powerplant into a liquid working fluid, the cooling circuit configured to transfer the heat energy received by the liquid working fluid into air flowing within the air duct to provide heated air, and the air duct extending from an airflow inlet towards an airflow exhaust;
an aircraft structure comprising an exterior surface; and
an anti-icing system configured to direct at least some of the heated air into the aircraft structure to heat the exterior surface, the anti-icing system including an anti-icing duct disposed between the cooling circuit and the airflow exhaust.
18. The aircraft system of claim 17 , wherein the liquid working fluid comprises lubricant.
19. The aircraft system of claim 17 , wherein the aircraft structure is remote from the powerplant.
20. An aircraft system, comprising:
an open propulsor rotor;
a powerplant configured to drive rotation of the open propulsor rotor, the powerplant including a thermal engine and an exhaust duct configured to exhaust combustion products generated by the thermal engine out of the powerplant;
a cooling system including a cooling circuit and an air duct, the cooling circuit configured to extract heat energy from the thermal engine and transfer the heat energy into air flowing within the air duct to provide heated air, the air duct disposed outside of the powerplant and downstream of the open propulsor rotor, and the air duct including an airflow exhaust disposed downstream of the cooling circuit;
an aircraft structure comprising an exterior surface; and
an anti-icing system configured to direct at least some of the heated air into the aircraft structure to heat the exterior surface, the anti-icing system including a bleed inlet disposed between the cooling circuit and the airflow exhaust.