Abstract: An aircraft cooling system includes a first coolant stream which cools at least one first heat load and a second coolant stream which cools at least one second heat load. The aircraft cooling system is formed such that the first heat load and the second heat load are thermally coupled together. The first heat load and the second heat load can be formed by two mutually redundant aircraft components. A third coolant stream thermally couples the first heat load and the second heat load together. The third coolant stream can be cooled by a heat sink, such as the outer skin of the aircraft in a bilge 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 aircraft cooling system evaporator arrangement has an evaporation device including four evaporators that are hydraulically separate from each other with respect to coolant flow. Refrigerant flows from a feed line into first and second evaporators, from the first evaporator into and through a third evaporator, and from the second evaporator into and through a fourth evaporator. The first and third evaporators define a first pair of evaporators arranged parallel to a second pair of evaporators defined by the second and fourth evaporators. First and second coolant supply lines of a first coolant circuit supply coolant to one of the evaporators in each of the first and second pair of evaporators respectively, and first and second coolant supply lines of a second, independent coolant circuit supply coolant to the other of the evaporators in each of the first and second pair of evaporators respectively.

Abstract: An aircraft cooling system evaporator arrangement has at least two mutually independent coolant circuits, at least two evaporation devices arranged to be hydraulically parallel for enabling an exchange of heat between the coolant and a refrigerant, at least two supply lines for supplying refrigerant to the evaporation devices, and at least two discharge lines for discharging refrigerant from the evaporation devices. A different one of the evaporation devices, a different one of the supply lines and a different one of the discharge lines are assigned to each of the coolant circuits, and the supply lines are hydraulically separate from each other as are the discharge lines. At least one refrigerant sensor monitors a refrigerant state of each of the discharge lines and an expansion valve is driven in accordance with the refrigerant sensors to control streams of refrigerant through the supply lines.

Abstract: An aircraft air-conditioning system is disclosed, which includes at least one heat exchanger to which coolant circulating in a cooling circuit of a cooling system and air are fed. The coolant cools the fed air in the heat exchanger, and the air leaving the heat exchanger enters the aircraft cabin. The coolant of the cooling system is always in the liquid state in the cooling circuit. The liquid coolant can also cool an aircraft seat or a sitting area of the aircraft seat.

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 dispenser of cooled or heated liquid which in one embodiment is a server cart for an aircraft. To avoid the need for a pump, the reservoir has a cooling or heating heat exchanger that helically coils around the main reservoir, which cools from the top down or heats from the bottom up, forming a counter current. The reservoir is connected to at least two conduits, one near the cooler top of the reservoir and one near the relatively warmer bottom of the reservoir. The two conduits connect to one another at a distance from the reservoir forming a dispensing passage, thereby allowing fluid to constantly circulate through the dispensing passage due to difference in the specific gravity in the fluid caused by the temperature difference. The elimination of the pump device is especially desirable for weight sensitive environments such as an aircraft.

Abstract: The present invention relates to an aircraft cooling system evaporator arrangement (10) with at least two mutually independent circuits (20a, 20b) for a coolant, at least two evaporation devices (12a, 12b) arranged to be hydraulically parallel for enabling an exchange of heat between the coolant and a refrigerant, at least two supply lines (18a, 18b) for supplying refrigerant to the evaporation devices (12a, 12b), and at least two discharge lines (22a, 22b) for discharging refrigerant from the evaporation devices (12a, 12b). One of the evaporation devices (12a, 12b), one of the supply lines (18a, 18b) and one of the discharge lines (22a, 22b) is assigned to each coolant circuit (20a, 20b).

Abstract: The present invention relates to an aircraft cooling system evaporator arrangement (10) with an evaporation device (20) for exchanging heat between a refrigerant and a coolant, the evaporation device (20) including at least four evaporators (24a, 24b, 24c, 24d) which are hydraulically separate from one another with respect to flow of coolant. The evaporator arrangement (10) further includes at least one feed line (26) for supplying refrigerant to the evaporation device (20). The evaporators (24a, 24b, 24c, 24d) are arranged in such a way that the evaporators (24a, 24b, 24c, 24d) are flowed through pairwise in parallel by refrigerant supplied to the evaporator by the feed line (26). Moreover, two mutually independent circuits (16, 17) for a coolant are provided, each coolant circuit including at least two supply lines (34a, 34c; 36b, 36d) arranged to be hydraulically separate from one another for supplying coolant to, in each instance, one of the evaporators (24a, 24b, 24c, 24d).

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 aircraft cooling system (1) according to the invention comprises a first coolant stream (4a) which cools at least one first heat load (2a), and a second coolant stream (4b) which cools at least one second heat load (2b), wherein the aircraft cooling system (1) is formed such that the first heat load (2a) and the second heat load (2b) are thermally coupled together. The first heat load (2a) and the second heat load (2b) can be formed by two mutually redundant aircraft components. A third coolant stream (12) can thermally couple the first heat load (2a) and the second heat load (2b) together. The third coolant stream (12) can be cooled by a heat sink (16).

Abstract: The present invention relates to a cooling device (20) for installation in an aircraft, in particular a passenger aircraft. The cooling device (20) comprises a heat exchanger (26) configured for flow-through of a liquid coolant for pre-cooling a cooling chamber (34) of the cooling device (20) to a temperature of the liquid coolant, the heat exchanger (26) being coupled in a heat-transferring manner to a refrigerant (28) which is in thermal contact with the cooling chamber (34) of the cooling device (20) for cooling the cooling chamber (34) to a temperature which is below the temperature of the liquid coolant, wherein the heat exchanger (26) and the refrigerant (28) are disposed inside the cooling chamber (34) of the cooling device (20), and wherein the heat exchanger (26) is configured for connection to a liquid coolant supply system installed on board the aircraft.

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 device for providing a cooled or heated liquid, in particular cooled drinking water comprises a reservoir for receiving the liquid to be cooled or to be heated. The reservoir is thermally coupled with a conduit through which a cooling medium or a heat transfer medium may flow and comprises a first as well as a second circulation connection, with the first circulation connection being connected with the second circulation connection via a circulation conduit.

Abstract: An aircraft air-conditioning system is disclosed, which includes at least one heat exchanger (14) to which coolant circulating in a cooling circuit of a cooling system and air are fed. The coolant cools the fed air in the heat exchanger (14), and the air leaving the heat exchanger (14) enters the aircraft cabin. The coolant of the cooling system is always in the liquid state in the cooling circuit. The liquid coolant can also cool an aircraft seat (2) or a sitting area of the aircraft seat (2).

Abstract: Cooling system and cooling method for cooling components of a power electronics The invention relates to a cooling system for cooling components (10) of power electronics installed on board an aircraft, in particular a passenger aircraft, comprising a cooling device (30) which is to be coupled in a heat-transmitting and planar manner to the components of the power electronics, and which cooling device (30) comprises at least two heat sinks (32, 34, 36, 38, 39, 50) fluidly isolated from one another, the cooling system further comprising at least two cooling circuits each including a cooling fluid source, wherein the at least two heat sinks of the cooling device (30) can be separately supplied with cooling fluids from different cooling fluid sources, and wherein the cooling system is configured such that no phase transition of the cooling fluids within the cooling circuits occurs, during operation of the cooling system. The invention also relates to a method for cooling components of power electronics.