초록 ▼

The present invention relates to an air-conditioning system, in particular an air-conditioning system for the air-conditioning of a passenger cabin of an airplane, having at least one heat exchanger arranged in a stagnation air passage for the cooling of compressed air and having at least one first

The present invention relates to an air-conditioning system, in particular an air-conditioning system for the air-conditioning of a passenger cabin of an airplane, having at least one heat exchanger arranged in a stagnation air passage for the cooling of compressed air and having at least one first shaft device and one second shaft device, with the heat exchanger including at least one first heat exchanger unit and one second heat exchanger unit separate from it on the compressed air side, which are arranged in the common stagnation air passage and of which a respective one is in communication on the compressed air side with a respective one of the shaft devices, with the shaft devices having compressors which are in respective communication on the outlet side with the inlet of the heat exchanger units on the compressed air side. The compressors are acted on by stagnation air or environmental air on the inlet side and are driven by means of one or more motors. The invention further relates to a method for the preparation of air for the air-conditioning of a space.

대표청구항 ▼

The invention claimed is: 1. An air-conditioning system, in particular an air-conditioning system for the air-conditioning of a passenger cabin of an airplane, having at least one heat exchanger arranged in a stagnation air passage, having at least one shaft device in communication with the heat ex

The invention claimed is: 1. An air-conditioning system, in particular an air-conditioning system for the air-conditioning of a passenger cabin of an airplane, having at least one heat exchanger arranged in a stagnation air passage, having at least one shaft device in communication with the heat exchanger at the compressed air side with at least one compressor acted on by stagnation air or environmental air at the inlet side and at least one turbine, having at least one motor for the driving of the compressor, having a turbine by-pass line for the bypassing of the turbine at the compressed air side and having at least one control device by means of which the air-conditioning system can be operated in a first operating mode in which the compressed air is expanded in the turbine and can be operated in a second operating mode in which the compressed air is guided predominantly or completely through the turbine bypass line, with the control device being in communication with the motor and being made such that the motor is operated in the first operating mode such that the motor power is used for cooling purposes and for pressurization and is operated in the second operating mode such that the motor power is used for the compression of the stagnation air or environmental air, said air conditioning system having at least one measuring device for measuring the throughflow of air from the heat exchanger. 2. An air-conditioning system in accordance with claim 1, having at least two heat exchanger units which form one constructional unit. 3. An air-conditioning system in accordance with claim 2, wherein a common stagnation air passage is provided for the at least two heat exchanger units. 4. An air-conditioning system in accordance with claim 3, wherein a stagnation air passage inlet valve whose position is adjustable is provided in the stagnation air inlet passage. 5. An air-conditioning system in accordance with claim 2, wherein a common stagnation air outlet passage is provided for the at least two heat exchanger units. 6. An air-conditioning system in accordance with claim 1, wherein at least two motor-driven blowers are provided in the stagnation air outlet passage. 7. An air-conditioning system in accordance with claim 6, wherein check valves are provided downstream of the blowers. 8. An air-conditioning system in accordance with claim 5, wherein one or more blower bypasses provided with a check valve are arranged in the stagnation air outlet passage. 9. An air-conditioning system in accordance with claim 1 comprising at least two compressors, wherein the compressors are multi-stage compressors of which the first stage is acted on by stagnation air or environmental air at the inlet side and the last stage is in communication at the outlet side with the inlet of the heat exchanger units at the compressed air side. 10. An air-conditioning system in accordance with claim 2 comprising at least two shaft devices, wherein the shaft devices each have at least one compressor, turbine and motor. 11. An air-conditioning system in accordance with claim 1 comprises at least two shaft devices, wherein each of the shaft devices is in communication with a respective water extractor circuit. 12. An air-conditioning system in accordance with claim 1 wherein the heat exchanger includes a first heat exchanger unit and a second heat exchanger unit separate from the first heat exchanger unit, and has a further third heat exchanger unit which can be acted on by stagnation air or environmental air and which is not in communication with the first and the second heat exchanger unit (12, 14) at the compressed air side. 13. An air-conditioning system in accordance with claim 1, wherein a cabin air circuit is provided in which means are arranged for the removal of heat from the air guided in the circuit. 14. An air-conditioning system in accordance with claim 13, wherein the means for the removal of heat include a heat exchanger. 15. An air-conditioning system in accordance with claim 13, wherein the means for the removal of heat include an evaporator. 16. An air-conditioning system in accordance with claim 12, wherein a fourth heat exchanger unit is arranged in the stagnation air passage and is made as a condenser and in communication with an evaporator, with the third heat exchanger unit and the evaporator being components of a refrigerant circuit. 17. An air-conditioning system in accordance with claim 12, wherein at least two bypass lines are provided which extend from the outlet side of the first and second heat exchanger units to the outlet side of the turbines and which can each be shut off by means of a valve arranged therein. 18. An air-conditioning system in accordance with claim 1, wherein the turbine (T) is in communication at the inlet side with the cabin or a mixing chamber disposed upstream thereof via a line closable by a valve (CSOV) and is in communication at the outlet side with the environment via a line closable by a valve (ASOV); and wherein means are provided by which the turbine (T) can be closed off from the lines guiding the air compressed in the compressor (C). 19. An air-conditioning system in accordance with claim 18, wherein the means are made as valves (TSOV, CKV) which are arranged in the inlet line connecting the turbine (T) to the mixing chamber or to the cabin. 20. A method for the preparation of air for the air-conditioning of a passenger cabin of an airplane, comprising the steps: a) compressing stagnation air or environmental air in a primary compressor unit and a secondary compressor unit, each driven by means of a respective motor and supplying the compressed air from each of said primary and secondary compressor units into a respective one of a first and a second heat exchanger; b) cooling of the air supplied to the first heat exchanger and second heat exchanger by stagnation air or environmental air, said first and second heat exchangers being arranged in separate respective air treatment circuits such that air passed through one of said heat exchangers does not pass through the other of said heat exchangers; wherein, in a first operating mode, the air cooled in the first heat exchanger is expanded in a first expansion stage without further compression, and air cooled in the second heat exchanger is cooled in a second expansion stage without further compression; wherein, in a second operating mode, the air cooled in the first heat exchanger is predominantly or completely guided past the first expansion stage in the bypass without passage through the second heat exchanger and air cooled in the second heat exchanger is predominantly or completely guided past the second expansion stage in the bypass without passage through the first heat exchanger; and wherein, in the first operating mode, the motor power is used for cooling purposes and for pressurization and, in the second operating mode, the motor power is used for the compression of the stagnation air or environmental air. 21. A method in accordance with claim 20, wherein the first operating mode of the method is used in ground operation of the airplane and at low altitudes of the airplane and the second operating mode is used in altitudes higher with respect to the former. 22. A method in accordance with claim 20, wherein cooling power on the cooling of the air supplied to the heat exchanger units by stagnation air or environmental air is controlled or regulated by the change of the position of a stagnation air passage inlet valve and/or by the change of the power of blowers arranged in the stagnation air outlet passage. 23. A method in accordance with claim 20, wherein the cabin air is at least partly guided in the circuit and is cooled in the process. 24. A method in accordance with claim 23, wherein the cooling takes place by means of a cooling medium which is guided in the circuit; and wherein heat is removed from the cooling medium in a heat exchanger unit arranged in the stagnation air passage of the air-conditioning system. 25. A method in accordance with claim 20, wherein, in the second operating mode, vitiated cabin air is expanded in a turbine (T) and is then supplied to the environmental air. 26. An air-conditioning system in accordance with claim 1, wherein the control device is made such that the first operating mode is used in ground operation and/or at low altitudes and the second operating mode is used at altitudes higher with respect to the former. 27. The air-conditioning system of claim 1 wherein the measuring device is a venturi element. 28. An air conditioning system for conditioning the air of a passenger cabin of an aircraft, said air conditioning system comprising: a) a two-part heat exchanger arranged in a stagnation air passage, said two-part heat exchanger having a first section and a second section which is separate from the first section; b) a first air treatment circuit which includes a first motor driven shaft device having a first compressor and a first turbine, a compressed air line in communication with the first section of the two-part heat exchanger and a first turbine bypass line for bypassing the turbine with at least a portion of the air exiting from the first section of the two-part heat exchanger, wherein in a first mode of operation at least a portion of the air exiting from the first section of the two-part heat exchanger is conducted through the first turbine bypass line, and in a second mode of operation at least a portion of the air exiting the first section of the two-part heat exchanger is conducted into the first turbine; and c) a second air treatment circuit which is separate from the first air treatment circuit and includes a second motor driven shaft device having a second compressor and a second turbine, a compressed air line in communication with the second section of the two-part heat exchanger and a second turbine bypass line for bypassing the turbine with at least a portion of the air exiting from the second section of the two-part heat exchanger, wherein in a first mode of operation at least a portion of the air exiting from the second section of the two-part heat exchanger is conducted through the second turbine bypass line, and in a second mode of operation at least a portion of the air exiting the second section of the two-part heat exchanger is conducted into the second turbine.