Patent ID: 11919647
Assignee: THE BOEING COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 18:
19. A thermal control system for an aircraft, the thermal control system comprising:
a first diffusor defining a first cavity to be positioned over a first rim of a first wheel of a landing gear, the first cavity to receive heat generated by the first wheel when the landing gear is in a retracted position;
a first duct coupled to the first diffusor, the first duct defining a first inlet fluidly coupled to the first cavity of the first diffusor;
a second diffusor defining a second cavity to be positioned over a second rim of a second wheel of the landing gear, the second cavity to receive heat generated by the second wheel when the landing gear is in the retracted position;
a second duct coupled to the first diffusor, the second duct defining a second inlet fluidly coupled to the second cavity of the second diffusor;
a main duct defining an outlet in fluid communication with the atmosphere, the main duct fluidly coupling the first inlet of the first duct and the second inlet of the second duct to the outlet.