대표
청구항
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1. An aircraft air conditioning system with at least one compressor (C), comprising a first conduit (10) which is connected with the pressure side of the compressor (C) and in which one or more cooling means provided downstream of the compressor (C) are arranged for cooling the air compressed in the compressor (C),a single turbine (T) arranged in the first conduit (10), anda second conduit designed as bypass conduit (20), which is connected with the pressure side of the compressor (C) and arranged such that it conducts at least part of the air compressed...
1. An aircraft air conditioning system with at least one compressor (C), comprising a first conduit (10) which is connected with the pressure side of the compressor (C) and in which one or more cooling means provided downstream of the compressor (C) are arranged for cooling the air compressed in the compressor (C),a single turbine (T) arranged in the first conduit (10), anda second conduit designed as bypass conduit (20), which is connected with the pressure side of the compressor (C) and arranged such that it conducts at least part of the air compressed in the compressor (C) in a bypass around at least one of the cooling means and with said single turbine (T) arranged in said first conduit (10) just upstream of the return junction with said second conduit (20), whereina bypass throttle means (TCV_H) is arranged in the bypass conduit (20), by which the mass flow of the air conducted through the bypass conduit (20) can be varied,in the first conduit (10) a first throttle means (TCV_C, VTN) is arranged, by which the mass flow of the air conducted through the first conduit (10) can be varied,a single unit (ECU) is provided, which is designed such that it can be operated in a first operating mode, second operating mode, or both first and second operating modes,in the first operating mode, when opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) is increased, the unit (ECU) effects reduction of opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10),inversely, when opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) is reduced, the unit (ECU) effects increase of opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10),in the second operating mode, the unit (ECU) effects increase of opening of both the bypass throttle means (TCV_H) provided in the bypass conduit (20) and first throttle means (TCV_C, VTN) provided in the first conduit (10) or reduction of opening of both the bypass throttle means (TCV_H) provided in the bypass conduit (20) and first throttle means (TCV_C, VTN) provided in the first conduit (10), andwith pressure at an outlet of said compressor (C) remaining essentially constant in all said operating modes. 2. The aircraft air conditioning system according to claim 1, wherein the unit (ECU) is designed such that the change of the openings of both throttle means (TCV_C, TCV_H) is effected with a pressure at the compressor outlet remaining constant when the openings are changed. 3. The aircraft air conditioning system according to claim 1, wherein the compressor (C) is arranged such that it is supplied with ambient or ram air or with precompressed air. 4. The aircraft air conditioning system according to claim 1, wherein the unit (ECU) is designed as a temperature control unit operating in the first operating mode and that there are provided one or more temperature sensors (30) connected with the temperature control unit, which measure the temperature of the air in the aircraft air conditioning system, wherein the temperature control unit is designed such that upon detection of a deviation between the actual temperature value measured by the temperature sensor(s) (30) and a specified desired temperature value it varies the opening of the throttle means (TCV_H) provided in the bypass conduit (20) for the purpose of reducing the control deviation. 5. The aircraft air conditioning system according to claim 4, wherein the bypass conduit (20) opens into the first conduit (10) and the one or more temperature sensors (30) in the first conduit (10) are arranged before, behind or both before and behind an orifice point of the bypass conduit (20) opening into the first conduit (10). 6. The aircraft air conditioning system according to claim 1, wherein the cooling means provided in the first conduit (10) are formed by a heat exchanger (HX) cooled with ram or ambient air and/or by a vapor cycle and/or by a turbine (T) for expanding air compressed in the compressor (C). 7. The aircraft air conditioning system according to claim 1, wherein the turbine (T) expands air compressed in the compressor (C) and a water separation circuit is provided upstream of the turbine (T). 8. The aircraft air conditioning system according to claim 1, wherein the turbine (T) and compressor (C) are seated on a shaft. 9. The aircraft air conditioning system according to claim 8, wherein the compressor (C), the turbine (T) and a motor (M) are all seated on the shaft. 10. The aircraft air conditioning system according to claim 1, wherein at least one motor (M) connected with the compressor (C) is provided for driving the compressor (C). 11. The aircraft air conditioning system according to claim 1, wherein the compressor (C) is of the one-stage or multi-stage type. 12. The aircraft air conditioning system according to claim 1, wherein the throttle means (TCV_H) provided in the bypass conduit (20) and the throttle means (TCV_C) provided in the first conduit (10) are designed as separate components or are formed by one common assembly. 13. The aircraft air conditioning system according to claim 1, wherein a mass flow control unit (ECU) is provided for controlling the mass flow through the aircraft air conditioning system, one or more flow rate measuring means (40) connected with the mass flow control unit as well as actuators are provided, by which the mass flow can be varied. 14. The aircraft air conditioning system according to claim 13, wherein the actuator(s) is(are) formed by means for adjusting the speed of a motor (M) driving the compressor (C). 15. The aircraft air conditioning system according to claim 13, wherein the mass flow control unit (ECU) and the temperature control unit (ECU) are formed by different components or by a controller. 16. The aircraft air conditioning system according to claim 1, wherein the bypass conduit (20) opens into the first conduit (10) downstream of the turbine (T). 17. The aircraft air conditioning system according to claim 1, configured such that in the first operating mode, pressure at the pressure side of the compressor (C) remains substantially constant and independent of degree of opening of the bypass throttle means (TCV_H), and in the second operating mode, transmittance of air conditioning is respectively increased or reduced. 18. The aircraft air conditioning system according to claim 1, additionally comprising at least one temperature sensor (30) arranged to indicate actual temperature value and forward the same to said unit (ECU), whereinsaid unit (ECU) is configured to open or close said bypass throttle means (TCV_H) when the actual temperature value is below or above a desired temperature value and, at the same time, close or open said first throttle means (TCV_C) to maintain the pressure at the outlet of said compressor (C) substantially constant. 19. A method of operating an aircraft air conditioning system, in particular an aircraft air conditioning system with a compressor (C), comprising a first conduit (10) which is connected with the pressure side of the compressor (C) and in which one or more cooling means provided downstream of the compressor (C) are arranged for cooling the air compressed in the compressor (C),a single turbine (T) arranged in the first conduit, anda second conduit designed as bypass conduit (20), which is connected with the pressure side of the compressor (C) and arranged such that it conducts at least part of the air compressed in the compressor (C) in a bypass around at least one of the cooling means and with said single turbine (T) arranged in said first conduit (10) just upstream of the return junction with said second conduit (20), whereina bypass throttle means (TCV_H) is arranged in the bypass conduit (20), by which the mass flow of the air conducted through the bypass conduit (20) can be varied,in the first conduit (10) a first throttle means (TCV_C, VTN) is arranged, by which the mass flow of the air conducted through the first conduit (10) can be varied,a single unit (ECU) controls opening and closing of both said first and bypass throttle means (TCV_C, VTN: TCV_H), andwhen increasing an opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) a reduction of an opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10) is effected and,inversely, when reducing the opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) an increase of the opening of the throttle means (TCV_C, VTN) provided in the first conduit (10) is effected, orwhen increasing the opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) an increase of the opening of the throttle means (TCV_C, VTN) provided in the first conduit (10) is effected, andwhen reducing the opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20), a reduction of the opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10) is effected,such that pressure at an outlet of said compressor (C) remains essentially constant in all said opening and closing combinations of said first and bypass throttle means (TCV_C, VTN; TCV_H). 20. The method according to claim 19, wherein the openings of the throttle means (TCV_C, TCV_H) are changed such that the pressure at the compressor outlet is not changed by changing the openings of the throttle means (TCV_C, TCV_H). 21. The method according to claim 19, wherein the temperature of the air flowing through the aircraft air conditioning system is measured and compared with a desired value, and in the case of a deviation between desired value and actual value, a change of the opening of the throttle means (TCV_H) provided in the bypass conduit (20) is performed for the purpose of temperature control. 22. The method according to claim 21, wherein the bypass conduit (20) opens into the first conduit (10) at an orifice point, and the temperature measurement is performed downstream or upstream of the orifice point. 23. The method according to claim 21, wherein the aircraft air conditioning system has a water separation circuit including a reheater (REH), condenser (COND), and water separator (WE), and the temperature measurement is effected between the water separator (WE) and the reheater (REH). 24. The method according to claim 19, wherein independent of the temperature control a control of the mass flow of the compressor outlet air is effected.
