Patent ID: 8656727

Claim:
A cooling system for an aircraft subsystem, comprising: a coolant loop configured to move a coolant through a heat-producing subsystem; a dehumidifying mechanism operative to receive bleed air and partition the bleed air into a dehumidified air stream and a humidified air stream; and a cooling mechanism positioned within the coolant loop downstream from the heat-producing subsystem and comprising a first inlet for receiving the dehumidified air stream, a second inlet for receiving the coolant from the heat-producing subsystem, an evaporative mechanism operative to introduce the coolant to the dehumidified air stream to evaporate a portion of the coolant into the dehumidified air stream, creating a reduced-temperature coolant and a re-humidified air stream, a first outlet for discharging the re-humidified air stream, and a second outlet for discharging the reduced-temperature coolant into the coolant loop upstream of the heat-producing subsystem.