|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F28C-001/00 B60H-001/32 F25D-017/06|
|미국특허분류(USC)||062/121; 062/244; 062/092; 244/135R; 261/127|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 51|
Apparatus, systems, and methods provide for the cooling of an aircraft subsystem. Coolant is routed through a heat-producing subsystem to absorb heat from the subsystem and to maintain the subsystem at a desired temperature. Bleed air from an aircraft engine is cooled, dehumidified, and routed to a cooling mechanism. In the cooling mechanism, a portion of the heated coolant is evaporated into the dehumidified bleed air, cooling the remaining coolant. The reduced-temperature coolant is routed back to the subsystem to absorb further heat. Humid air from th...
1. 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; anda 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 ope...