Abstract: An aircraft cooling system including a cooler having a cold transfer circuit, in which a cold transfer medium circulates. The cooler supplies cooling energy to an aircraft device to be cooled. The aircraft cooling system further includes a heat transfer arrangement having a heat transfer circuit, in which a heat transfer medium circulates and which is thermally coupled to the cold transfer circuit of the cooler via a heat exchanger, in order to absorb waste heat generated by the cooler and transfer it to a cabin air extraction system. The heat transfer arrangement further includes at least one heat pump which brings about an increase of the heat energy transfer from the cold transfer medium circulating in the cold transfer circuit of the cooler to the heat transfer medium circulating in the heat transfer circuit, at least in certain operating phases of the aircraft cooling system.

Abstract: An aircraft cooling system including a cooler which is adapted to supply cooling energy to an aircraft device to be cooled, and a heat transfer arrangement which is adapted to transfer waste heat generated by the cooler to a cabin air extraction system. The heat transfer arrangement comprises a heat transfer circuit, in which a liquid heat transfer medium heated by the waste heat of the cooler circulates.

Abstract: A pipe treatment system for a supply unit is provided. The pipe treatment system comprises a fresh water inlet pipe, a tap for fresh water, a controllable tap valve, and a control device for the pipe treatment control system. The controllable tap valve is arranged between the fresh water inlet pipe and the tap for fresh water. The control device for the pipe treatment control system is connected to the controllable tap valve so as to place the controllable tap valve in a pipe treatment state when there is a pipe treatment signal at the control device, so as to provide a more reliable pipe treatment system, for example for disinfection or descaling.

Abstract: A cooling system is provided for a combustion engine having at least one pressure sensor and a diaphragm. The diaphragm is impermeable to a coolant of the cooling system and in contact with the coolant on a first side. A sensor device of the at least one pressure sensor is arranged separated from the coolant on a second side of the diaphragm located opposite the first side and configured to determine a pressure of the coolant.

Abstract: Cooling of an electronic device in an aircraft by case-by-case single-phase or two-phase cooling There is proposed a method for cooling an electronic device in an aircraft (11), comprising the following steps: circulating a coolant in a cooling circuit, cooling the electronic device (2) by means of the coolant, and in an aircraft outer-shell heat exchanger, emitting the heat taken up by the coolant. The coolant evaporates, at least partially, during the cooling of the electronic device (2), and condenses in the aircraft outer-shell heat exchanger (7). The coolant circulates in the coolant circuit by natural convection.

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.