US 12,358,631 B2
Aircraft thermal anti-icing system
Francois Belleville, Varennes (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Dec. 13, 2022, as Appl. No. 18/080,514.
Prior Publication US 2024/0190573 A1, Jun. 13, 2024
Int. Cl. B64D 15/04 (2006.01); B64D 29/00 (2006.01); B64D 33/02 (2006.01); B64D 33/08 (2006.01); B64D 27/24 (2006.01)
CPC B64D 15/04 (2013.01) [B64D 29/00 (2013.01); B64D 33/02 (2013.01); B64D 33/08 (2013.01); B64D 27/24 (2013.01); B64D 2033/0233 (2013.01)] 20 Claims
OG exemplary drawing
 
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.