Abstract: A system for ventilating an explosion hazard region of an aircraft includes a ram-air channel, which has an air inlet for feeding ambient air into the ram-air channel as well as an air outlet. The ram-air channel is devised to feed air to a device that is to be cooled on board the aircraft. A ventilation line has an air inlet for feeding air flowing through the ram-air channel into the ventilation line as well as an air outlet. The ventilation line is devised to feed air to a region of the aircraft that is to be ventilated. An accumulator is disposed between the ram-air channel and the air inlet of the ventilation line and is devised to convert the dynamic pressure of the air flow conveyed through the ram-air channel at least partially into static pressure for regulating flow through the explosion hazard region.

Abstract: The invention relates to a refrigerating device (10), in particular for an aircraft, having a refrigerant circuit, in which a refrigerant container (12), an expansion valve (14), an evaporator (16), a compressor (20) and a condenser (22) are disposed. To save energy during operation and to increase the reliability and availability of the refrigerating device (10), in the refrigerant circuit there is a compressor bypass line (26), in which a bypass valve (18) is disposed, and a refrigerant pump (30) that is disposed downstream of the condenser (22) and upstream of the evaporator (16). It is possible to dispense with the refrigerant pump (30) if the condenser (22) is disposed at a higher level than the evaporator (16) in the refrigerant circuit.

Abstract: An air duct for supplying ambient air in an aircraft includes an air inlet, a flow duct portion and a feed device that is devised to feed ambient air through the air inlet and the flow duct portion. A flow control flap closes the air inlet in a first position, releases a first flow cross-section of the air inlet in a second position and releases a larger second flow cross-section of the air inlet in a third position. The flow control flap is designed to not increase drag significantly in the second position while still enabling flow through the flow duct portion, while increasing drag to increase air fow through the flow duct portion in the third position.

Abstract: An aircraft cooling system for cooling heat loads on board an aircraft includes a cold producing device, a first cold carrier fluid circuit thermally coupled to the cold producing device and connected to a first heat load in order to carry off heat from the first heat load, a second cold carrier fluid circuit connected to a second heat load in order to carry off heat from the second heat load, a heat exchanger disposed in the second cold carrier fluid circuit and configured to thermally couple the second cold carrier fluid circuit to an ambient temperature surrounding the aircraft, and a coupling system configured to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit.

Abstract: A system (10) for ventilating an explosion hazard region (12) of an aircraft comprises a ram-air channel (16), which has an air inlet for feeding ambient air into the ram-air channel (16) as well as an air outlet (18). The ram-air channel (16) is devised to feed air to a device that is to be cooled on board the aircraft. A ventilation line (22) has an air inlet (24) for feeding air flowing through the ram-air channel (16) into the ventilation line (22) as well as an air outlet (26). The ventilation line (22) is devised to feed air to a region (12) of the aircraft that is to be ventilated. An accumulator (28) is disposed between the ram-air channel (16) and the air inlet (24) of the ventilation line (22) and is devised to convert the dynamic pressure of the air flow conveyed through the ram-air channel (16) at least partially into static pressure.

Abstract: The invention relates to an air duct (10) for supplying ambient air in an aircraft, comprising an air inlet (12), a flow duct portion (16) extending downstream of the air inlet (12) and a feed device (22) that is devised to feed ambient air through the air inlet (12) and the flow duct portion (16). A flow control flap (24) closes the air inlet (12) in a first position, releases a first flow cross-section of the air inlet (12) in a second position and releases a second flow cross-section of the air inlet (12), which is larger than the first flow cross-section, in a third position.

Abstract: The invention relates to a refrigerating device (10), in particular for an aircraft, having a refrigerant circuit, in which a refrigerant container (12), an expansion valve (14), an evaporator (16), a compressor (20) and a condenser (22) are disposed. To save energy during operation and to increase the reliability and availability of the refrigerating device (10), in the refrigerant circuit there is a compressor bypass line (26), in which a bypass valve (18) is disposed, and a refrigerant pump (30) that is disposed downstream of the condenser (22) and upstream of the evaporator (16). It is possible to dispense with the refrigerant pump (30) if the condenser (22) is disposed at a higher level than the evaporator (16) in the refrigerant circuit.

Abstract: A cooling system for cooling heat loads on board an aircraft comprises a cold producing device, a first cold carrier fluid circuit, which is thermally coupled to the cold producing device and is connected to a first heat load in order to carry off heat from the first heat load, and a second cold carrier fluid circuit, which is connected to a second heat load in order to carry off heat from the second heat load. A coupling system of the cooling system is adapted to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit. In a method for operating such a cooling system for cooling heat loads on board an aircraft, the first cold carrier fluid circuit is selectively thermally coupled to the second cold carrier fluid circuit or thermally uncoupled from the second cold carrier fluid circuit by means of the coupling system.

Abstract: A compensating tank for a cooling circuit of an internal combustion engine has at least one inflow connection and one outflow connection, both of which are connected with the cooling circuit, a chamber system formed in the tank to receive the coolant, such that the individual chambers are at least partially interconnected via openings, and a coolant pipe connected with the inflow connection discharging into one of the chambers in which an impact element is provided for the inflowing coolant. The impact element is configured as a curved guiding wall along which the inflowing coolant is specifically guided. This inhibits, among other things, foaming of the coolant flowing into the compensating tank.