Patent ID: 8191834
Filing Date: 2012-06-05
Classification: B64C,B64D,Y02T

Abstract:
1. A cooling system for an aircraft, the cooling system comprising: a suction unit for removing, by suction through suction air apertures, boundary layer air from a flow-critical surface of the aircraft; a heat exchanger for cooling a medium, through which heat exchanger the boundary layer air that has been removed by suction flows; and a ram-air channel comprising a closed-loop control device and a ram-air channel flap regulated by the closed-loop control device, wherein the closed-loop control device comprises a temperature sensor upstream or downstream of the heat exchanger for determining measuring data for the cooling system; wherein the closed-loop control device and the ram-air channel flap are adapted to regulate an airstream of ram air flowing through the ram-air channel in order to add ram air flowing through the ram-air channel to the boundary layer air upstream of the heat exchanger and thus before both the ram-air and the boundary layer air are fed to the heat exchanger to increase the cooling output of the cooling system when the closed-loop control device determines from the measuring data for the cooling system that removing the boundary layer air by suction through the air apertures is not efficient enough and thus the cooling output of the cooling system has to be increased; wherein the boundary layer air that has been removed by suction and the ram air are used as a coolant that flows through the heat exchanger.