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

Claim 11:
12. A thermal control system for use with an aircraft, the thermal control system comprising:
a conduit defining a fluid passageway between an inlet and an outlet, the inlet of the conduit positioned in fluid communication with a landing gear wheel well, the outlet of the conduit positioned in fluid communication with the atmosphere, the conduit to generate a pressure differential through the fluid passageway between the inlet and the outlet to exhaust heat from the landing gear wheel well to the atmosphere; and
an eductor in fluid communication with the fluid passageway, the eductor to provide high pressure bleed air downstream from the inlet to generate the pressure differential through the fluid passageway to cause air from the wheel well to flow from the inlet toward the outlet.