초록 ▼

A system (10) for cooling a thermally loaded device on board an aircraft comprises a distribution line (12) which is in communication with an installation space (14) of the thermally loaded device, a coolant supply line (20) which is in communication with a coolant source, and a heat removal line (2

A system (10) for cooling a thermally loaded device on board an aircraft comprises a distribution line (12) which is in communication with an installation space (14) of the thermally loaded device, a coolant supply line (20) which is in communication with a coolant source, and a heat removal line (28) which is in communication with a source of pressure below atmospheric pressure. A shut-off control device (34) is adapted so as, in a first position, to separate the distribution line (12) from the coolant supply line (20) and connect the distribution line (12) to the heat removal line (28) and, in a second position, to connect the distribution line (12) to the coolant supply line (20) and separate the distribution line (12) from the heat removal line (28).

대표청구항 ▼

The invention claimed is: 1. System (10) for cooling a thermally loaded device on board an aircraft, comprising a distribution line (12) which is in communication with an installation space (14) of the thermally loaded device, a coolant supply line (20) which is in communication with a coolant sour

The invention claimed is: 1. System (10) for cooling a thermally loaded device on board an aircraft, comprising a distribution line (12) which is in communication with an installation space (14) of the thermally loaded device, a coolant supply line (20) which is in communication with a coolant source, a heat removal line (28) which is in communication with a source of pressure below atmospheric pressure, and a shut-off control device (34) which is adapted so as, in a first position, to separate the distribution line (12) from the coolant supply line (20) and connect the distribution line (12) to the heat removal line (28) and, in a second position, to connect the distribution line (12) to the coolant supply line (20) and separate the distribution line (12) from the heat removal line (28), characterized in that the coolant supply line (20) is connected to a region of a ram-air channel (22) to which a pressure above atmospheric pressure is applied, and in that the heat removal line (28) is connected to a region of the ram-air channel (22) to which a pressure below atmospheric pressure is applied. 2. Cooling system according to claim 1, characterized in that the coolant supply line (20) is connected to the ram-air channel (22) upstream of heat exchangers (24, 26) disposed in the ram-air channel (22). 3. Cooling system according to claim 1, characterized in that the heat removal line (28) is connected to the ram-air channel (22) upstream of a fan (30) disposed in the ram-air channel (22) and downstream of the heat exchangers (24, 26) disposed in the ram-air channel (22). 4. Cooling system according to claim 1, characterized in that the shut-off control device (34) comprises an adjustable flap (36), which is adapted so as, in the first position of the shut-off control device (34), to block the coolant supply line (20) and clear the heat removal line (28) and, in the second position of the shut-off control device (34), to clear the coolant supply line (20) and block the heat removal line (28). 5. Cooling system according to claim 1, characterized in that in the distribution line (12) openings (18) and/or nozzles (17) are formed for connecting the distribution line (12) to the installation space (14) of the thermally loaded device. 6. Method for cooling a thermally loaded device on board an aircraft, comprising the steps moving the shut-off control device (34) of a system according to one of claims 1 to 5 into a first position in order during operation of the aircraft on the ground to separate the distribution line (12) from the coolant supply line (20) and to connect the distribution line (12) to the heat removal line (28), and moving the shut-off control device (34) into a second position in order during operation of the aircraft in flight to connect the distribution line (12) to the coolant supply line (20) and to separate the distribution line (12) from the heat removal line (28). 7. Method according to claim 6, characterized in that the shut-off control device (34) during operation of the aircraft in flight on conclusion of the take-off phase is moved from its first position into its second position.