Patent Abstract:
A system for air-conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer, a first recirculation system designed to remove exhaust air from a first aircraft cabin region and connected to the central mixer, and a second recirculation system designed to remove exhaust air from a second aircraft cabin region and connected to a local mixer. A control device is designed to control the second recirculation system to reduce an air volume flow being removed from the second aircraft cabin region when shifting from a first operating state (e.g., normal operation) to a second operating state (e.g., defined operating situations such as when quick cooling is desired). The air volume being removed from the first aircraft cabin region may be increased accordingly in the second operating state.

Full Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application claims priority, under Section 371, to PCT Application No. PCT/EP2009/005361, filed on Jul. 23, 2009, which claims priority to German Application No. 10 2008 035 123.7 and also to U.S. Provisional Application No. 61/083,976, both filed on Jul. 28, 2008. 
    
    
     TECHNICAL FIELD 
     The present invention relates to a system and a method for air-conditioning an aircraft cabin. 
     BACKGROUND 
     The cabin of a modern passenger aircraft is air-conditioned usually both when the aircraft is flying and is on the ground by means of the aircraft&#39;s own air conditioning system. The aircraft air conditioning system is supplied with bleed air which is taken from the engine compressors or auxiliary power unit compressors and cooled to a desired low temperature in the air conditioning units, the so-called air conditioning packs of the aircraft air conditioning system. The air cooled in the air conditioning packs of the aircraft air conditioning system is led into a mixer where it is mixed with recirculation air sucked from the aircraft cabin. The mixed air produced in the mixer and composed of cold fresh air provided by the air conditioning packs and of recirculation air sucked from the aircraft cabin is finally led into the aircraft cabin for air-conditioning of the aircraft cabin 
     In wide-body aircraft, in particular in wide-body aircraft having two passenger decks extending over the entire length of the aircraft, an air conditioning system described, for example, in DE 44 25 871 C1 and comprising two recirculation systems for sucking exhaust air from the aircraft cabin is used at present. A low-pressure recirculation system extracts air from an upper deck region of the cabin, while a high-pressure recirculation system serves to extract air from a middle deck region of the cabin. The recirculation air removed from the middle deck region of the cabin by the high-pressure recirculation system is blown into a central mixer of the aircraft air conditioning system. In contrast, the air sucked from the upper deck region by the low-pressure recirculation system is supplied to local mixers which are fed with premixed air by the central mixer, i.e. an air mixture composed of cold fresh air provided by the air conditioning packs and recirculation air from the middle deck region of the cabin. The air mixture, produced in the local mixers, composed of premixed air from the central mixer and recirculation air from the upper deck region of the cabin is finally used for air-conditioning the aircraft cabin. In particular, air is led into the middle deck region of the cabin from a local mixer arranged in the region of the middle deck, while air is blown into the upper deck region of the cabin from a local mixer arranged in the region of the upper deck. 
     An air conditioning system equipped with two recirculation systems is designed so that both recirculation systems must always provide a defined minimum air flow in order to ensure sufficient ventilation of the aircraft cabin. In the operation of the aircraft air conditioning system, therefore, it is not possible to switch off one recirculation system or both recirculation systems. In the operation of the recirculation systems, however, the waste heat produced by the fans of the recirculation systems gives rise to additional heat loads. The cooling energy required for cooling the recirculation fans has to be provided by the air conditioning system, so that the operation of the recirculation systems reduces the cooling capacity available for the cooling of the aircraft cabin. 
     In particular when the aircraft is on the ground on hot days, the additional heat input of the recirculation systems can significantly increase the time required for cooling the aircraft cabin to a desired temperature. The air conditioning system then requires a longer run-up period until the cabin is sufficiently cooled and passenger boarding can start. As a result, the turnaround of the aircraft at the airport is slowed down. Since the air conditioning system is supplied with bleed air from the auxiliary power unit compressors in this operating phase, the increased run-up period of the air conditioning system also gives rise to increased fuel costs. Finally, the operating time of the auxiliary power unit is increased, which may lead to higher maintenance costs. 
     The invention is directed at the object of specifying a system and a method for air-conditioning an aircraft cabin which allow a shortening of the time required for cooling the aircraft cabin when the aircraft is on the ground. 
     SUMMARY 
     This object is achieved by a system for air-conditioning an aircraft cabin having the features described below and a method for air-conditioning an aircraft cabin having the features described below. 
     A system for air-conditioning an aircraft cabin according to the invention comprises an air conditioning unit connected to a central mixer in order to supply the central mixer with air at a desired low temperature. The air conditioning unit can be supplied with bleed air at an elevated pressure from the engine compressors or the auxiliary power unit compressors. A first recirculation system of the air conditioning system according to the invention is designed to remove exhaust air from a first aircraft cabin region. The first recirculation system can comprise a plurality of air outlet openings which are arranged in the first aircraft cabin region and are formed, for example, in a side-wall region near the floor or in a floor region of the first aircraft cabin region. The first recirculation system of the air conditioning system according to the invention is furthermore connected to the central mixer in order to lead the exhaust air removed from the first aircraft cabin region into the central mixer. 
     Furthermore, the air conditioning system according to the invention comprises a second recirculation system which is designed to remove exhaust air from a second aircraft cabin region. Similarly to the first recirculation system, the second recirculation system can also comprise a plurality of air outlet openings which are formed in a side-wall region near the floor or in a floor region of the second aircraft cabin region. In a wide-body aircraft having two passenger decks, the first aircraft cabin region can be, for example, a middle deck region of the aircraft cabin. The second aircraft cabin region can then be, for example, an upper deck region of the cabin. The second recirculation system is connected to a local mixer in order to lead the exhaust air from the second aircraft cabin region into the local mixer. Depending on the design of the system, the air conditioning system according to the invention can also comprise a plurality of local mixers. A system for air-conditioning the cabin of a wide-body aircraft having two passenger decks can comprise, for example, a first local mixer arranged in the region of the middle deck and a second local mixer arranged in the region of the upper deck. 
     The local mixer is connected to the central mixer. The mixed air produced in the central mixer and composed of cold fresh air provided by the air conditioning unit and recirculation air from the first aircraft cabin region can thus be led from the central mixer into the local mixer. In the local mixer, the mixed air supplied from the central mixer is finally also mixed with the recirculation air removed from the second aircraft cabin region, before the mixed air is led from the local mixer into the aircraft cabin. For example, mixed air from a first local mixer arranged in the region of the middle deck can be used to air-condition the middle deck region of the aircraft cabin, while mixed air from a local mixer arranged in the region of an upper deck can be employed to air-condition the upper deck region of the aircraft cabin. 
     The system for air-conditioning an aircraft cabin according to the invention furthermore comprises a control device which is designed to control the second recirculation system in the normal operation (also referred to as a “first operating state” in places below) of the air conditioning system in such a way that the second recirculation system removes a predefined air volume flow from the second aircraft cabin region. The control device can be, for example, an electronic control device. Preferably, the air volume flow removed from the second aircraft cabin region by the second recirculation system in the normal operation of the air conditioning system is approximately equal to the air volume flow removed from the first aircraft cabin region by the first recirculation system. 
     The control device of the system for air-conditioning an aircraft cabin according to the invention is also designed to control the second recirculation system in defined operating situations (also referred to as a “second operating state” in places below) of the air conditioning system in such a way that the air volume flow removed from the second aircraft cabin region by the second recirculation system is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region by the second recirculation system in the normal operation of the air conditioning system. In other words, the control device is designed to reduce the capacity of the second recirculation system in defined operating situations of the air conditioning system without, however, completely stopping the operation of the second recirculation system. 
     The idea underlying the present invention is based on the realization that in particular the additional heat load which arises owing to the waste heat produced by the fans of the second recirculation system has an adverse effect on the air conditioning capacity of the entire system. The cause of this effect is considered to be the fact that the exhaust air removed from the second aircraft cabin region, which air is additionally heated by the waste heat of the components of the second recirculation system, is supplied into the local mixer where it is not mixed with cold fresh air produced by the air conditioning unit, but merely with mixed air, already premixed and consequently preheated, from the central mixer before it is led back into the second aircraft cabin region. 
     As a result of the reduction of the air volume flow removed from the second aircraft cabin region by the second recirculation system, the amount of waste heat produced by the fans of the second recirculation system can be reduced. Moreover, less heat exhaust air from the second aircraft cabin region is supplied to the local mixer. This allows markedly more efficient utilization of the cold fresh air produced by the air conditioning unit. Operating situations in which a reduction of the capacity of the second recirculation system has an advantageous effect are, for example, situations in which quick cooling of the aircraft cabin is desired or required. 
     The air conditioning system according to the invention thus allows rapid cooling of the aircraft cabin also when the aircraft is on the ground on hot days. As a result, passenger boarding can start more quickly and thus the turnaround time of the aircraft at the airport can be shortened. Moreover, the operating times of the auxiliary power unit for supplying the air conditioning unit with bleed air are reduced, with the result that fuel savings and lower maintenance costs can be achieved. A further advantage of the air conditioning system according to the invention consists in the fact that it is weight-neutral, i.e. optimized utilization of the cooling capacity of the air conditioning unit is made possible without additional weight. 
     The control device of the air conditioning system according to the invention is preferably designed to evaluate at least one predefined parameter and to control the second recirculation system in dependence on the evaluation of the at least one predefined parameter. In particular, the evaluation of the at least one predetermined parameter serves to determine the utilization state of the air conditioning unit and components associated with the air conditioning unit. Furthermore, the evaluation of the at least one predetermined parameter can serve to detect the presence of an operating situation in which a reduction of the additional heat input caused by the second recirculation system is desired or required. The control device can control the second recirculation system in such a way that the air volume flow removed from the second aircraft cabin region by the second recirculation system is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region by the second recirculation system in the normal operation of the air conditioning system only if the air conditioning unit is not yet fully utilized, i.e. the air conditioning unit is still in an operating state in which it can still provide additional cooling capacity. As a result of such a control of the air conditioning system according to the invention, overloading of the air conditioning unit and components associated with the air conditioning unit is reliably prevented. 
     The parameter(s) evaluated by the control device can be, for example, a cabin temperature actual value for the first aircraft cabin region, a cabin temperature set value for the first aircraft cabin region, a cabin temperature actual value for the second aircraft cabin region, a cabin temperature set value for the second aircraft cabin region, an outside temperature actual value, a temperature actual value of the air provided by the air conditioning unit, a temperature set value of the air provided by the air conditioning unit, a temperature actual value of the air provided by the central mixer, a temperature set value of the air provided by the central mixer, a temperature actual value of the air provided by the local mixer and/or a temperature set value of the air provided by the local mixer. Furthermore, the control device of the air conditioning system according to the invention can be designed to evaluate various air volume flow actual and/or set values, for example, of the exhaust air removed from the first aircraft cabin region, of the exhaust air removed from the second aircraft cabin region, of the mixed air supplied to the local mixer by the central mixer and/or of the air conditioning air blown into the aircraft cabin by the local mixer. 
     Furthermore, the control device of the system for air-conditioning an aircraft cabin according to the invention can be designed to control the first recirculation system in such a way that the air volume flow removed from the first aircraft cabin region by the first recirculation system is increased in relation to a predefined air volume flow removed from the first aircraft cabin region by the first recirculation system in the normal operation of the air conditioning system. As a result of the increase of the exhaust air flow to be removed from the first aircraft cabin region, the quantity of recirculation air supplied to the central mixer is increased and the loss of recirculation air due to the reduction of the capacity of the second recirculation system is at least partly compensated. Although the amount of waste heat produced by the first recirculation system is increased by the increase of the capacity of the first recirculation system, the additional heat input produced by the first recirculation system has a very much smaller influence on the cooling capacity of the entire air conditioning system than the additional heat input produced by the second recirculation system in operation, since the air heated by the waste heat of the fans of the first recirculation system is led from the first aircraft cabin region directly into the central mixer and mixed with cold fresh air there. The cooling of the air in the aircraft cabin is therefore hardly slowed down by an increase of the capacity of the first recirculation system. 
     In a particularly preferred embodiment of the system for air-conditioning an aircraft cabin according to the invention, the control device is designed to control the first recirculation system in such a way that the air volume flow removed from the first aircraft cabin region by the first recirculation system is increased in relation to the predefined air volume flow removed from the first aircraft cabin region by the first recirculation system in the normal operation of the air conditioning system by an amount which is equal to the amount by which the air volume flow removed from the second aircraft cabin region by the second recirculation system is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region by the second recirculation system in the normal operation of the air conditioning system. In other words, the loss of recirculation air resulting from the reduction of the capacity of the second recirculation system is preferably completely compensated by additional recirculation air which is additionally sucked from the first aircraft cabin region by the first recirculation system owing to the increase in capacity of the first recirculation system. There is thus no reduction of the total recirculation air quantity, but merely a redistribution between the recirculation air quantity conveyed by the first recirculation system and the recirculation air quantity conveyed by the second recirculation system. As a result, a sufficiently high air exchange rate is ensured in the aircraft cabin in every operating state of the air conditioning system according to the invention. 
     In a method for air-conditioning an aircraft cabin according to the invention, air is produced at a desired low temperature by an air conditioning unit. The cold fresh air produced by the air conditioning unit is supplied into a central mixer. Exhaust air is removed from a first aircraft cabin region by a first recirculation system. The air removed from the first aircraft cabin region by the first recirculation system is led into the central mixer. Exhaust air is removed from a second aircraft cabin region by a second recirculation system. The air removed from the second aircraft cabin region by the second recirculation system is led into a local mixer. Mixed air from the central mixer is supplied to the local mixer. The second recirculation system is controlled by a control device, which can be, for example, in the form of an electronic control device, in the normal operation of the air conditioning system in such a way that the second recirculation system removes a predefined air volume flow from the second aircraft cabin region. In defined operating situations of the air conditioning system, the second recirculation system is controlled by the control device in such a way that the air volume flow removed from the second aircraft cabin region by the second recirculation system is reduced in relation to the air volume flow removed from the second aircraft cabin region by the second recirculation system in the normal operation of the air conditioning system. 
     Preferably, the control device evaluates at least one predefined parameter and controls the second recirculation system in dependence on the evaluation of the at least one predefined parameter. 
     For example, the control device evaluates a cabin temperature actual value for the first aircraft cabin region, a cabin temperature set value for the first aircraft cabin region, a cabin temperature actual value for the second aircraft cabin region, a cabin temperature set value for the second aircraft cabin region, an outside temperature actual value, a temperature actual value of the air provided by the air conditioning unit, a temperature set value of the air provided by the air conditioning unit, a temperature actual value of the air provided by the central mixer, a temperature set value of the air provided by the central mixer, a temperature actual value of the air provided by the local mixer and/or a temperature set value of the air provided by the local mixer and controls the second recirculation system in dependence on the evaluation of this/these parameter(s). 
     Preferably, the control device controls the first recirculation system in such a way that the air volume flow removed from the first aircraft cabin region by the first recirculation system is increased in relation to a predefined air volume flow removed from the first aircraft cabin region by the first recirculation system in the normal operation of the air conditioning system. 
     In a particularly preferred embodiment of the air conditioning method according to the invention, the control device controls the first recirculation system in such a way that the air volume removed from the first aircraft cabin region by the first recirculation system is increased in relation to the predefined air volume flow removed from the first aircraft cabin region by the first recirculation system in the normal operation of the air conditioning system by an amount which is equal to the amount by which the air volume flow removed from the second aircraft cabin region by the second recirculation system is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region by the second recirculation system in the normal operation of the air conditioning system. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       A preferred embodiment of the invention will now be explained in more detail with the aid of the accompanying schematic FIGURE, which shows a schematic illustration of a system for air-conditioning an aircraft cabin according to the invention. 
     
    
    
     DETAILED DESCRIPTION 
     In the FIGURE, a system  10  for air-conditioning an aircraft cabin  12  is shown. The aircraft cabin  12  comprises two passenger decks and consequently a first aircraft cabin region  12   a  formed by a middle deck of the aircraft cabin  12  and a second aircraft cabin region  12   b  formed by an upper deck of the aircraft cabin  12 . The air conditioning system  10  comprises an air conditioning unit  14  for producing cold fresh air which is supplied to a central mixer  16 . In the central mixer  16 , the cold fresh air produced by the air conditioning unit  14  is mixed with recirculation air which is removed from the first aircraft cabin region  12   a , i.e. the middle deck of the aircraft cabin region  12 , by a first recirculation system  18 . The exhaust air removal from the first aircraft cabin region  12   a  takes place through air outlet openings arranged in the floor region of the first aircraft cabin region. 
     The mixed air produced in the central mixer  16 , i.e. the mixture of cold fresh air and recirculation air conveyed by the first recirculation system  18  from the first aircraft cabin region  12   a  is supplied to a first and a second local mixer  20 ,  22 . The first local mixer  20  is arranged in the region of the middle deck of the aircraft cabin  12 , while the second local mixer  22  is arranged in the region of the upper deck of the aircraft cabin  12 . The local mixers  20 ,  22  are furthermore fed with recirculation air which is sucked from the second aircraft cabin region  12   b  by a second recirculation system  24 . The recirculation air removal from the second aircraft cabin region  12   b  takes place through air outlet openings arranged in a side-wall region of the second aircraft cabin region  12   b.    
     The air mixture produced in the first local mixer  20  is supplied to the first aircraft cabin region  12   a  as air conditioning air. Similarly, the air mixture produced in the second local mixer  22  is supplied to the second aircraft cabin region  12   b  as air conditioning air. Excess air from the aircraft cabin  12 , i.e. air from the first and the second aircraft cabin region  12   a ,  12   b  which is not supplied to the central mixer  16  or the local mixers  20 ,  22  from recirculation air, is removed from the aircraft cabin  12  into the environment via an air outlet valve  26 . 
     The first recirculation system  18  comprises fans, not illustrated specifically in the FIGURE, which produce waste heat in operation. Similarly, the second recirculation system  24  comprises fans, which are likewise not illustrated specifically in the FIGURE and produce waste heat in operation. The waste heat produced by the recirculation fans provides an additional heat input into the aircraft cabin  12  which has to be removed by the air conditioning system  10 . 
     The air conveyed from the first aircraft cabin region  12   a  by the fans of the first recirculation system  18  and additionally heated by the waste heat of the fans of the first recirculation system  18  is mixed directly with cold fresh air in the central mixer  16 . In contrast to this, the air conveyed from the second aircraft cabin region  12   b  by the second recirculation system  24  and additionally heated by the waste heat of the fans of the second recirculation system  24  is led into the local mixers  20 ,  22 , from where it is led back into the aircraft cabin  12  again after mixing with air which is already premixed. While the additional heat input produced by the fans of the first recirculation system  18  has hardly any influence on the efficiency of the entire system  10 , the cooling capacity of the entire system  10  is significantly impaired by the additional heat input caused by the fans of the second recirculation system  24 . In particular, the cooling process in the aircraft cabin is slowed down considerably. 
     The air conditioning system  10  furthermore comprises an electronic control device  20  which is designed to control the first and the second recirculation systems  18 ,  24 . The control device  28  evaluates a series of parameters which are provided to the control device  28  by various sensors and/or storage devices. In particular, the control device  28  can evaluate a cabin temperature actual value for the first aircraft cabin region  12   a , a cabin temperature set value for the first aircraft cabin region  12   a , a cabin temperature actual value for the second aircraft cabin region  12   b , a cabin temperature set value for the second aircraft cabin region  12   b , an outside temperature actual value, a temperature actual value of the air provided by the air conditioning unit  14 , a temperature set value of the air provided by the air conditioning unit  14 , a temperature actual value of the air provided by the central mixer  16 , a temperature set value of the air provided by the central mixer  16 , a temperature actual value of the air provided by the local mixers  20 ,  22  and/or a temperature set value of the air provided by the local mixers  20 ,  22 . 
     In a first operating state (the normal operation) of the air conditioning system  10 , the control device  28  controls the first recirculation system  18  in such a way that the first recirculation system  18  removes a predefined air volume flow from the first aircraft cabin region  12   a . Similarly, the control device  28  controls the second recirculation system  24  in the first operating state of the air conditioning system  10  in such a way that the second recirculation system  24  removes a predefined air volume flow from the second aircraft cabin region  12   b . If, in contrast, the control device  28  detects a second operating state, for example on the basis of the parameter evaluation which it has carried out, the presence of a defined operating situation of the air conditioning system  10 , i.e. for example an operating situation in which rapid cooling of the aircraft cabin  12  is desired or required, the control device  28  checks, by evaluating the parameters available to it, whether the air conditioning unit  14  is already being fully utilized or is still able to provide additional cooling energy. 
     If the control device  28  ascertains in the second operating state, on the basis of the parameter evaluation which it has carried out, that the air conditioning unit  14  is not yet being operated at full load and can still provide additional cooling capacity, the control device  28  controls the second recirculation system  24  in such a way that the air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  in the first operating state of the air conditioning system  10 . For example, the air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  can be reduced by 20% from the removal in the first operating state. The amount by which the air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  in the first operating state of the air conditioning system  10  is controlled by the electronic control unit  28  likewise in dependence on the result of the parameter evaluation which it has carried out. 
     If the second recirculation system  24  is operated at reduced capacity, the first recirculation system  18  is, in contrast, controlled by the electronic control unit  28 , again in dependence on the parameter evaluation which it has carried out, in such a way that the air volume flow removed from the first aircraft cabin region  12   a  by the first recirculation system  18  in the second operating state is increased in relation to the predefined air volume flow removed from the first aircraft cabin region  12   a  by the first recirculation system  18  in the first operating state of the air conditioning system  10  by an amount which is equal to the amount by which the air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  is reduced in relation to the predefined air volume flow removed from the second aircraft cabin region  12   b  by the second recirculation system  24  in the first operating state of the air conditioning system  10 . In other words, the control device  28  ensures a redistribution of the recirculation air conveying capacity between the first and the second recirculation system  18 ,  24 . 
     As a result of the increased conveying capacity of the first recirculation system  18 , the amount of waste heat produced by the fans of the first recirculation system  18  also increases. As already mentioned, the waste heat produced by the fans of the first recirculation system  18  can, however, be removed relatively easily, since the air heated by the waste heat can be mixed directly with cold fresh air in the central mixer  16 . Cooling capacity additionally provided by the air conditioning unit  14  can therefore be utilized very efficiently for removing this waste heat. As a result of the reduction of the capacity of the second recirculation system  24 , however, the additional heat input, produced by the fans of the second recirculation system  24 , into the recirculation air from the second aircraft cabin region  12   b  is markedly reduced. Thus, the air in the local mixers  20 ,  22  can also be cooled very much more quickly to a desired low temperature by mixing with premixed air from the central mixer  16 . As a result, the time which is required to cool the aircraft cabin  12  to a desired temperature when the aircraft is on the ground can be significantly shortened.

Technology Classification (CPC): 1