A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.
Adaptive trans-critical CO2 cooling systems for aerospace applications
01.08.2017
Patent
Elektronische Ressource
Englisch
ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS
Europäisches Patentamt | 2020
|Adaptive trans-critical CO2 cooling systems for aerospace applications
Europäisches Patentamt | 2016
|ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS
Europäisches Patentamt | 2019
|TRANS-CRITICAL CO2 COOLING SYSTEM FOR AEROSPACE APPLICATIONS
Europäisches Patentamt | 2015
|Trans-critical CO2 cooling system for aerospace applications
Europäisches Patentamt | 2020
|