• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention proposes an air conditioning system for aircraft powered solely by electrical energy, adapted to take air outside the aircraft and to deliver conditioned air inside the aircraft. The system comprises at most three motorized rotating machines which consist of a first and a second motorized turbocharger (11, 12) independent of each other, and a motor-compressor (13) interconnected between the motorized turbochargers (11, 12). The motor compressor (13) is arranged to generate a primary air flow, which causes a secondary air flow, allowing the cooling of a flow of air to breathe in a first phase of operation; be stationary or idle in a second phase of operation; and, provide additional airflow to breathe in a third phase of operation.
    公开号:FR3025497A1
    申请号:FR1458359
    申请日:2014-09-05
    公开日:2016-03-11
    发明作者:Guillaume Galzin；Vincent Gomez
    申请人:Liebherr Aerospace Toulouse SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates generally to an air conditioning system. The invention finds applications, in particular, in the field of aeronautics. It concerns more particularly the context of the "more electric" aircraft. PRIOR ART Airplanes marketed today include three sources of secondary energy generated from the combustion of primary energy, that is to say kerosene. These secondary energies are hydraulic energy, pneumatic energy and electrical energy. They are used to power various loads on board the aircraft. Current research tends to substitute for these three secondary energy sources a single source of electrical energy. This is called "more electric" aircraft. However, with the transition to the "more electric" aircraft, some systems must be modified to adapt to the disappearance of hydraulic and / or pneumatic energy. This is the case of the air conditioning system that currently uses pneumatic energy by drawing compressed air directly into the propulsion engines of the aircraft. The air conditioning system has several functions: to ensure a certain flow of fresh air in the pressurized zone (to ensure a sufficient oxygen turnover rate for the occupants and a sufficient amount of air for the pressurization system), Dry air sent to the pressurized zone and provide air conditioning and heating functions. Solutions already exist to adapt the air conditioning system to the context of the "more electric" aircraft. A first solution presents an air conditioning system which is currently embarked on the latest of the large aircraft of a North American manufacturer, including a first part of sampling and compression 3025497 2 of the outside air and a second part of conditioning the air taken. The sampling and compression part consists of four motor-compressors and the conditioning part consists of two packs each comprising a turbocharger. This first solution therefore comprises five rotating machines. A second solution, described in US Pat. No. 7,797,962, is composed of two packs ensuring both the collection of the outside air, its compression and conditioning, and each comprising a motor-compressor and a motorized turbocharger. This second solution 10 then comprises four rotating machines. Rotating machines are heavy and cumbersome. In addition, they are generally expensive, and need to be driven by complex power electronics. Their large number complicates the architecture which generates indirect costs of development and maintenance. SUMMARY OF THE INVENTION The invention aims at alleviating all or part of the disadvantages of the aforementioned prior art. The object of the present invention is to propose a new air conditioning system architecture consuming only electrical energy as secondary energy generated on board an aircraft. The present invention aims to reduce the number of rotating machines used to reduce the complexity, weight, size and cost of the system.
    [0002] For this purpose, a first aspect of the invention proposes an air conditioning system for aircraft powered solely by electrical energy, adapted to take air from outside the aircraft and to deliver conditioned air to the aircraft. inside the aircraft. The air conditioning system comprises at most three motorized rotating machines which consist of: first and second independent motorized turbochargers, each powered turbocharger being formed of a compressor, a turbine and an electric motor; and 3025497 3 - a motor-compressor interconnected between the motorized turbochargers via an interconnection pipe and formed of a compressor and an electric motor, and wherein the motor-compressor is arranged to: 5 - generate a flow of primary air, which causes a flow of secondary air, allowing the cooling of a flow of air to breathe in a first phase of operation, corresponding to a phase of operation on the ground or at relatively low altitude and relatively low speed of the aircraft; Being stationary or idling in a second phase of operation at relatively low altitude and relatively high speed of the aircraft; and, providing additional airflow to breathe in a third phase of operation at relatively high altitude and relatively high speed of the aircraft. Such an air conditioning system comprising only three motorized rotating machines, that is to say two motorized turbochargers and a motor-compressor, is particularly well suited for sampling, pressurizing and conditioning the outside air and 20 brings to the system, directly, significant savings in weight, size and cost. The air conditioning system also has a simplified architecture. In addition, such an air conditioning system is then electrically powered only by three supply channels only, each feeding one of the respective rotating machines. Thus, reducing the number of rotating machines and electrical channels indirectly reduces the complexity, bulk, mass and cost of the electrical system and therefore potentially reduces the overall fuel consumption of the electrical system. plane. Advantageously, the motor-compressor has two distinct but complementary functions, used alternately according to the different phases of operation of the aircraft. In addition, several system configurations can be implemented to introduce redundancy, in order to remedy possible failures of this motor-compressor.
    [0003] The system thus proposed makes it possible to eliminate a motor-compressor compared to systems of the prior art while improving the energy efficiency of the air-conditioning system without sacrificing its efficiency or its robustness compared with the previous ones. possible breakdowns.
    [0004] For the sake of optimizing the invention, the interconnection pipe may also be adapted to, in the third phase of operation, substantially equal parts of the compressed air flow respectively provided by the compressor of each motorized turbocharger, from the air compressed by the motor-compressor. In an advantageous embodiment, the interconnection pipe comprises at least two isolation valves each positioned between the motor-compressor and a respective one of the motorized turbochargers, said isolation valves being adapted to allow the balancing of the system. 15 in a nominal operating mode and its reconfiguration in a degraded operating mode in case of failure. Thus, the closing of the isolation valves in the third phase makes it possible to isolate one of the motorized turbochargers or the motor-compressor in the event of failure of one of these machines. The isolation valves thus advantageously permit control of the air flow supplied by the motor-compressor and also maintain the functional system in the event of failure of a rotating machine. In some embodiments, the air conditioning system further comprises at least one input plenum adapted to supply air to the compressors of the powered rotating machines from at least one Ramair input. Having a centralized air inlet allows both to simplify and balance the air conditioning system. According to one embodiment, the air conditioning system comprises: at least one first and one second differential unit each associated with a respective one of the motorized turbochargers and each comprising an air injection device powered with in the air by the motor-compressor in the first phase of operation; at least one first and one second heat exchanger, each associated with a respective one of the motorized turbochargers and a respective one of the pressure-reducing members, each heat exchanger being adapted to cool the air to breathe therethrough; using a secondary air flow generated by the associated offset member. In addition, each pressure-reducing member is adapted to ventilate the respective motorized turbocharger and in which at least one of the pressure-reducing members is adapted to, in addition, ventilate the motor-compressor. Therefore, the motor-compressor associated with the two pressure-reducing members advantageously allows to create a secondary air flow for cooling the air to breathe sent into the pressurized zone, in the first phase.
    [0005] Advantageously, the air conditioning system may also comprise at least four ventilation valves adapted to regulate the ventilation of the system through the pressure-reducing members, a first ventilation valve being positioned to make a connection between the first and second ventilation valves. the first motorized turbocharger, a second vent valve being positioned to make a connection between the first pressure-reducing member and the motor-compressor, a third vent valve being positioned to make a connection between a second pressure-reducing member and the second one; motorized turbocharger and a fourth vent valve being positioned to make a connection between the second pressure-reducing member and the motor-compressor. Consequently, the closing and / or opening of the ventilation valves makes it possible to isolate the motor-compressor in the event of a failure of the latter and thus to create a redundancy of equipment by using the air supplied by the compressors of the compressors. motorized turbochargers for supplying the pressure-reducing members.
    [0006] In the interest of comfort, the air conditioning system may comprise at least a first and a second air drying device, each being associated with a respective one of the motorized turbochargers as well as with the a respective one of the exchangers. The dewatering device makes it possible to dehumidify the air before sending it to a pressurized zone. In order to save energy, the air conditioning system may furthermore comprise at least a first and a second altitude valve, each of which makes it possible to avoid a respective one of the dewatering devices as well as the turbine of the motorized turbocharger associated with said dewatering device. Indeed, when the outside air is not wet, it is not necessary to dry it. This is the case, for example for system operation during a high altitude flight phase. Such an air conditioning system may be such that its power supply is provided by a power supply network including a power supply channel for each powered rotating machine. Each supply channel is then connected to one of the rotating machines. There are therefore three power supply networks only, instead of four in the prior art.
    [0007] Brief Description of the Drawings Other features and advantages of the invention will become apparent upon reading the following description. This is purely illustrative and should be read in conjunction with the accompanying drawings in which: - Figure 1 is a block diagram showing an air conditioning system according to embodiments of the invention; FIG. 2 is a functional diagram showing an air conditioning system, in a first phase of operation, according to one embodiment of the invention; FIG. 3 is a block diagram showing an air conditioning system, in a second phase of operation, according to one embodiment of the invention; FIG. 4 is a functional diagram showing an air conditioning system, in a third phase of operation, according to one embodiment of the invention. DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 illustrates the general structure of an embodiment of an air conditioning system 10 according to embodiments of the present invention. The function of the air conditioning system 10 is to ensure a certain air flow rate in the pressurized zone (with a certain rate of oxygen renewal), to pressurize the pressurized zone, and possibly to dry the air sent. to the pressurized zone and, in addition, to provide heating and air conditioning functions. The air supplied to the pressurized zone may consist partly of air supplied by the system 10, called air to breathe, and partly of recirculating air, that is to say of the air air taken from the pressurized zone, which is filtered before being reinjected. The system 10 can be embarked on board a "more electric" aircraft. In such an application, the system 10 comprises, for example, two sampling and air conditioning packs. A first pack comprises a motorized turbocharger 11 and a second pack comprises another motorized turbocharger 12. In addition, a single motor-compressor 13 is associated with the two motorized turbochargers via an interconnection pipe (shown in the figures by a doubled solid line). . The air conditioning system 10 then comprises three motorized rotating machines. In the example shown in FIG. 1, the motorized turbocharger 11 comprises a compressor 14, an electric motor 17 and a turbine 20; likewise the motorized turbocharger 12 comprises a compressor 15, an electric motor 18 and a turbine 21; finally, the motor-compressor 13 comprises a compressor 16 and an electric motor 19.
    [0008] 3025497 8 A compressor consumes energy to compress air; on the contrary, a turbine expands air by providing energy. Thus the compressors 14, 15 consume electrical energy converted into mechanical energy by the motors 17, 18 respectively, as well as the pneumatic energy transformed into mechanical energy by the turbines 20, 21 respectively. The compressor 16 consumes, for its part, only electrical energy transformed into mechanical energy by the engine 19. In this example, the first pack further comprises a heat exchanger 22, a dewatering device 24 and a depressing element 26.
    [0009] Similarly, the second pack comprises a heat exchanger 23, a dewatering device 25, and a pressure reducing member 27. The air conditioning system 10 draws outside air (shown in the figures as a bold arrow) ), preferably via a Ramair input 29 associated with a centralized input plenum 28. The collected air is then distributed by the plenum 28 between the various components of said system 10 as needed. In an alternative embodiment, the collection of outside air could be done using several inputs, for example an input for each component using this air. The withdrawn air is then distributed to the two packs, preferably in an equal manner. In the following description, only the operation of the first pack will be described but the operation of the second pack is identical to that of the first pack. Once the outside air is pressurized by the two packs, the latter is injected into the pressurized zone of the aircraft via an internal outlet 30. Part 25 of the outside air taken off which is not pressurized, is rejected to it. the outside of the aircraft via an external output 31. The external output 31 is, in this example, a Ramair output. On a typical aircraft flight profile, the air conditioning system described has three distinct phases. A first phase of operation, referred to as the ground phase, is a phase of operation on the ground or at a relatively low altitude and at a relatively low speed. A second phase of operation is a flight phase at relatively low altitude and relatively high speed. The second phase of operation can therefore be identified in the phases of the beginning of climb or end of descent of the aircraft as well as the waiting and approach phases of the aircraft that precede the landing. Finally, a third phase of operation, called cruise phase, is a flight phase at relatively high altitude and relatively high speed. The third phase of operation can therefore be identified at the end of climb or start of descent phases of the aircraft as well as at the cruise flight phase. The altitude corresponding to the transition between the second phase and the third phase as well as the speed corresponding to the transition between the first phase and the second phase depend on the sizing of the packs, and more precisely the sizing of the compressors, as well as the characteristics from the plane. In particular, the speed of the aircraft can be considered as high speed when this speed is sufficient for self-ventilation of the system, that is to say to cause the secondary air flow. The invention is not limited by the value of altitude and speed. Referring to Figure 2, the air conditioning system 10 is first shown in the first floor phase. The airflow to be breathed (shown in the figures by a thin line), which is the air injected into the pressurized zone, is therefore taken outside the aircraft via the Ramair input 29 and distributed via the plenum 28 in the first pack and in parallel with the second pack. The compressor 14 of the motorized turbocharger 11 then compresses the flow of air to breathe. This has the consequence of increasing the pressure and the temperature of the air passing through it, the increase in temperature being directly related to the increase of the air pressure. The airflow to be breathed is then cooled through the exchanger 22. It is then dehumidified by passing through the dewatering device 24 forming a water separation loop. The latter comprises, for example, a heater 32, a condenser 34 and a water extractor 36. Similarly, the dewatering device 25 of the second pack comprises a heater 33, a condenser 35 and a water extractor 37.
    [0010] Finally, the flow of air to breathe passes through the turbine 20 of the motorized turbocharger 11 in order to be relaxed before returning to the condenser 34 of the dewatering device 24 to be injected into the pressurized zone via the internal outlet 30. .
    [0011] Thus, in the ground operation phase, the two motorized turbochargers 11, 12 each provide, for example, about half of the total breathing airflow supplied in the pressurized zone. The exchanger 22 therefore aims to cool the air before it is injected into the pressurized zone. To do this, the secondary air flow 10 (shown in the figures by a thick solid line), having a temperature colder than that of the air to be breathed, can exchange by conduction with the flow of air to breathe in the air. exchanger. The airflow to be breathed is then cooled while the secondary air stream is warmed up. The secondary air flow comes from outside the aircraft, via the Ramair inlet 29, and is rejected outside the aircraft, via the external outlet 31, after passing through the exchanger 22 to evacuate the heat. In order to create the secondary air flow passing through the exchanger 22, the depressor element 26 is positioned between the outlet of the exchanger 22 and the external outlet 31. In this embodiment of the invention, the member 20 Depressor 26 is a trunk. Similarly, the depressive member 27 of the second pack may also be a horn. However, in another exemplary embodiment, the pressure-reducing members 26, 27 could be ventilators such as electric fans. The function of the pressure-reducing member 26 is to create a depression 25 to drive the air upstream of said member and thus create the movement of the secondary air flow from the plenum 28 to the external outlet 31. To create the depression in the frame of a pressure-type negative-displacement member, air having a higher pressure than the air to be drawn corresponding to the primary air can be injected, via an injector, into the pressure-reducing member 26 towards the outlet external 31.
    [0012] 302 54 9 7 11 In the first phase, the motor-compressor 13 provides compressed air from the outside air to the injector. Indeed, the compressor 16 compresses the air distributed by the plenum 28 and via a ventilation valve 38 provides a primary air flow (shown in the figures by a dashed dotted line) to the injector. Similarly, the compressor 16 supplies air to the injector of the depressurizing member 25 of the second pack via a ventilation valve 39. In addition, in the ground phase, the compressor 16 consumes the electrical energy converted into energy. mechanical by the associated electric motor 19. The energy consumed by the compressor 14 is, in part, the electrical energy converted into mechanical energy by the associated motor 17 and, in part, the pneumatic energy converted into mechanical energy by the associated turbine 20. Electric motors need to be cooled. For this, a ventilation air flow (shown in the figures by a bold dotted line) passes through the three motors 17, 18, 19. This flow of ventilation air comes from the outside of the aircraft, by example via the plenum 28, and is rejected outside the aircraft, for example via the external outlet 31. The flow of ventilation air can be driven during the ground phase, in the same way as the secondary air flow, that is to say by the deprimogenic members 26, 27.
    [0013] Referring to Figure 3, the air conditioning system 10 is shown in the second phase of operation of the aircraft between ground operation and high altitude flight operation. In this second phase, the operation of the air conditioning system 10 remains generally the same as in the first phase. However, in the second phase, the aircraft moves at a higher speed than in the first phase. Thus, the secondary air flow no longer needs to be driven by the vacuum units 36, 37. The same is true for the ventilation air flow. Indeed, the air is driven by the Ramair dynamic pressure generated by the speed of the aircraft. The ventilation valves 38, 39, 40, 41 are closed and there is therefore no more primary air flow supplied by the motor-compressor 13.
    [0014] Thus, in this second phase, the motor-compressor 13 can operate at an idle speed or even be stopped in order to save the electrical energy available on board the aircraft. Referring to Figure 4, the air conditioning system 10 is shown in the third cruise phase, or high altitude flight phase. In the cruising phase the plane moves at high speed as in the second phase. Thus, the secondary air flow and the ventilation air flow do not need to be driven by the vacuum units 36, 37. Moreover, in the cruising phase, the outside air has a more low pressure and lower temperature compared to outside air from other phases. The high altitude outside air is also dry, so it is not necessary to dry it through the dewatering devices 24, 25. Thus in the cruise phase, an altitude valve 44 which is positioned between the outlet of the exchanger 22 and the internal outlet 30 can be opened to allow the flow of air to breathe to be directly injected into the pressurized zone without passing through the dewatering device 24 and the turbine 20 via an altitude line (represented in the figures by a dotted line). Similarly for the second pack, an altitude valve 45 which is positioned between the outlet of the exchanger 23 and the internal outlet 30 can be opened to deflect the flow of air to breathe and allow it to be directly injected in the pressurized zone without passing through the dewatering device 25 and the turbine 21. During the ground phase and the second phase, these altitude valves 44, 45 are generally closed. In the cruising phase, the turbines 20, 21 which no longer function, therefore do not supply energy to the respective associated compressors 14, 15. The motors 17, 18 then provide the compressors 14, 15 respectively associated all the energy required.
    [0015] Given the properties of the air at altitude and the volumetric flow capacities of the compressors, the total flow rate supplied in the pressurized zone must be shared on the three compressors 14, 15, 16. To do this, the motor-compressor 13, which from the second phase no longer provides the primary air flow, is then used to supplement the flow rates of air to be injected into the pressurized zone of each motorized turbocharger 11, 12. additional air flow injected into the pressurized zone and thus compensate for the lower density of the outside air. Thus, an isolation valve 42 positioned between the air outlet of the compressor 14 and that of the compressor 16 is opened to allow the motor-compressor 13 to supply air at the inlet of the exchanger 22. Similarly, for the second pack, an isolation valve 43 positioned between the stream of compressed air leaving the compressor 15 and the one leaving the compressor 16, is opened to allow the motor-compressor 13 to supply air input of the heat exchanger 23. During the ground phase and the second phase, these isolation valves 42, 43 are closed. The motor-compressor 13 is thus connected via the interconnection line to the two motorized turbochargers 11, 12. Preferably, the air supplied by the compressor 16 is shared equally between the first pack and the second pack. The three compressors 14, 15, 16 preferably each provide one third of the total air flow. In addition, the isolation valves 42, 43 have a balancing function since they also make it possible to balance the flow of air supplied by the two packs.
    [0016] The air-conditioning system 10 may further comprise a plurality of devices which, in the event of failure of one of the system components or packs, i.e. when the system is no longer in operation. nominal operating mode but in degraded operating mode, reconfigure it to allow it to operate despite the or faults.
    [0017] For example, in the first phase of operation, in the event of failure of the motor-compressor 13 or in the event of rupture of the interconnection pipe, the ventilation valve 38 may be closed to isolate the motor-compressor 13 from the compressor. two packs. Another vent valve 40 positioned between the compressor 14 of the motorized turbocharger 11 and the pressure reducing member 26 is open so that said compressor 14 provides the primary air flow to said member. Thus part of the flow of air to breathe is deflected to the pressure reducing member 26 before reaching the exchanger 22. Similarly, a ventilation valve 41 is positioned between the compressor 15 of the motorized turbocharger 12 and the pressure reducing member 27. If this same failure of the motor-compressor 13 or the interconnect line occurs in the cruising phase, then only the two motorized turbochargers provide air to breathe in the pressurized zone. The flow of air injected into the pressurized zone is reduced but remains acceptable from the point of view of the safety of the aircraft and its occupants. In the event of failure of one of the packs, the isolation valves 42, 43 may be closed, independently of one another, to isolate the defective pack. The operation of the system remains the same in the first and second phases. During the third phase, the functional pack is then supercharged by all the air flow coming from the motor-compressor. Flow in the pressurized zone is also reduced, irrespective of the flight phase of the aircraft, but remains acceptable. Finally, in the event of failure of one of the motorized turbochargers 11, 12, the latter is isolated by means of the isolation valves 42, 43. The system can then operate as in the event of a failure of a pack by itself. serving the remaining motorized turbocharger and the motor-compressor. A different solution during the cruising phase may be to shunt the defective motorized turbocharger by isolating it by a valve positioned at the outlet of its compressor and to direct the air flow, supplied by the motor-compressor, into the engine. exchanger of the pack of said turbocharger to take advantage of the cold air capacity of the two packs.
    [0018] The present invention thus makes it possible to ensure the proper functioning of an air conditioning system while reducing the number of rotating machines and providing for sufficient redundancies to guarantee the operation of said system, and guaranteeing a level of efficiency. and sufficient quality of air distribution. Reducing the number of rotating machines irreversibly leads to a reduction in the costs and complexity of the system and makes it possible to optimize the entire architecture of the air conditioning system. The architecture of such a system is then simplified. The system is more reliable and reduces the maintenance required while ensuring the same level of availability of treated air. The three rotating machine conditioning system 10 is used in "more electric" aeronautical applications. This air conditioning system can, in particular, find applications on all ranges of aircraft, for example business jets or any type of commercial aircraft (single aisle, regional, long range, ...) . Of course, the present invention is not limited to the preferred embodiment and the embodiments presented above by way of non-limiting examples. It also relates to the variants within the scope of those skilled in the art within the scope of the claims below.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Aircraft air conditioning system powered solely by electrical energy, adapted to withdraw air from outside the aircraft and to deliver conditioned air to the interior of the aircraft, comprising at most three motorized rotating machines which consist of: - a first and a second motorized turbocharger (11, 12) independent of each other, each motorized turbocharger being formed of a compressor (14, 15), a turbine (20, 21) ) and an electric motor (17, 18); and - a motor-compressor (13) interconnected between the motorized turbochargers (11, 12) via an interconnecting line and formed of a compressor (16) and an electric motor (19), and wherein the motorcycle compressor (13) is arranged to: - generate a primary air flow, which causes a secondary air flow, allowing the cooling of a flow of air to breathe in a first phase of operation, corresponding to a phase of operation on the ground or at relatively low altitude and relatively low speed of the aircraft; - Being stopped or idling in a second phase of operation at relatively low altitude and relatively high speed of the aircraft; and, - provide additional airflow to breathe in a third phase of operation at relatively high altitude and relatively high speed of the aircraft.
    [0002]
    2. An air conditioning system according to claim 1, wherein the interconnection pipe is adapted for, in the third phase of operation, substantially equal parts equal to the flow rate of compressed air respectively provided by the compressor (14). , 15) of each motorized turbocharger (11, 12), from the air compressed by the motor-compressor (13). 3025497 17
    [0003]
    An air conditioning system according to claim 1 or claim 2, wherein the interconnecting conduit comprises at least two isolation valves (42, 43) each positioned between the motor-compressor (13) and the a respective one of the motorized turbochargers (11, 12), said isolation valves being adapted to allow the balancing of the system in a nominal operating mode and its reconfiguration in a degraded operating mode in case of failure.
    [0004]
    An air conditioning system according to any one of claims 1 to 3, further comprising at least one input plenum (28) adapted to supply air outside the compressors (14, 15, 16). motorized rotating machines from at least one Ramair entry (29).
    [0005]
    5. An air conditioning system according to any one of claims 1 to 4, comprising: - at least a first and a second pressure-reducing members (26, 27) each associated with a respective one of the motorized turbochargers (11, 12) and each comprising an air injection device supplied with air by the motor-compressor (13) in the first phase of operation; At least one first and one second heat exchanger (22, 23), each associated with a respective one of the motorized turbochargers (11, 12) and a respective one of the pressure reducing members (26, 27), each exchanger heat being adapted to cool the air to breathe through it with the aid of the secondary air stream generated by the associated imimogene body. 25
    [0006]
    An air conditioning system according to claim 5, wherein each pressure reducing member (26, 27) is adapted to ventilate the respective motorized turbocharger (11, 12) and wherein at least one of the pressure reducing members (26, 27) is adapted to further ventilate the motor compressor (13).
    [0007]
    An air conditioning system according to claim 5 or 6, further comprising at least four ventilation valves (38, 39, 40, 41) adapted to regulate the ventilation of the system through the pressure reducing members (26, 27), a first vent valve (40) being positioned to make a connection between the first vacuum member (26) and the first motorized turbocharger (11), a second vent valve (38) being positioned to make a connection between the first negative-pressure element (26) and the motor-compressor (13), a third ventilation valve (41) being positioned to make a connection between a second pressure-reducing member (27) and the second motorized turbocharger (12) and a fourth valve the ventilation device (39) being positioned to make a connection between the second pressure-reducing member (27) and the motor-compressor (13).
    [0008]
    An air conditioning system according to any of claims 1 to 7, comprising at least first and second air dewatering devices (24, 25), each associated with a respective one motorized turbochargers (11, 12) and a respective one of the exchangers (22, 23).
    [0009]
    The air conditioning system of any one of claims 1 to 8, further comprising at least a first and a second elevation valve (44, 45), each for disconnecting a respective one of the devices. dewatering (24, 25) and the turbine (20, 21) of the motorized turbocharger (11, 12) associated with said dewatering device. 25
    [0010]
    10. An air conditioning system according to any one of claims 1 to 9, wherein the power supply is provided by a power supply network comprising a power supply channel for each motorized rotating machine.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3194270B1|2018-08-29|Air conditioning system for a "more electric" airplane
    EP2780230B1|2015-09-30|Method and architecture for recovery of energy in an aircraft
    EP2714515B1|2015-07-08|Air conditioning system for an aircraft passenger compartment
    FR3009278A1|2015-02-06|METHOD FOR REGULATING THE DEFROSTING OF AN AIRCRAFT ATTACHMENT EDGE AND DEVICE FOR IMPLEMENTING THE SAME
    FR2936224A1|2010-03-26|SYSTEM FOR MANAGING THE THERMAL FLOW OF AN AIRCRAFT.
    CA2888717C|2020-10-27|Air conditioning method and system for aircraft
    FR2923462A1|2009-05-15|METHOD FOR MANAGING THERMAL REJECTIONS GENERATED BY AN AIRCRAFT AND COOLING DEVICE FOR AN AIRCRAFT FOR CARRYING OUT SAID METHOD.
    EP3418194A1|2018-12-26|System and method for environmental control of an aircraft cabin and aircraft provided with such a control system
    WO2014135812A1|2014-09-12|Nacelle equipped with an oil-cooling circuit comprising an intermediate heat exchanger
    FR2486210A1|1982-01-08|AIR CYCLE AIR CONDITIONING SYSTEM
    EP3342709A1|2018-07-04|Method and device for environmental control of an aircraft supplied with bleed air at intermediate pressure
    EP3466816A1|2019-04-10|Autonomous module for recovering energy from an aircraft cabin and corresponding method
    EP3521589A1|2019-08-07|System for cooling engine air with two cooling stages and corresponding method
    FR3048231B1|2019-07-05|SYSTEM COMPRISING A HYBRID AIR CONDITIONING UNIT FOR AN AIRCRAFT CAB
    FR3066754A1|2018-11-30|AIR CONDITIONING SYSTEM OF AN AIRCRAFT CAB AND METHOD OF OPERATION THEREOF
    EP3521590A1|2019-08-07|System for cooling engine air with two cooling stages and comprising at least one cylindrical heat exchanger
    WO2020254755A1|2020-12-24|Aircraft cabin electrical air conditioning system comprising a motorized compressor and an air cycle turbomachine
    FR3103140A1|2021-05-21|Cabin air conditioning system of an air or rail transport vehicle using a pneumatic and thermal air source separate from the air conditioning source
    FR3041607A1|2017-03-31|PRESSURIZED AIR SUPPLY UNIT FOR AIRCRAFT
    FR3089204A1|2020-06-05|Air management system especially for air conditioning and defrost pack
    CA3144727A1|2021-01-28|Air conditioning system with cabin air recovery
    WO2022028992A1|2022-02-10|Driven turbocompressor of an air conditioning system, having optimized cooling
    FR3042173A1|2017-04-14|METHOD AND DEVICE FOR AIR CONDITIONING OF AN AIRCRAFT CAB AND AIRCRAFT IN WHICH THIS DEVICE IS IMPLEMENTED
    WO2020201654A1|2020-10-08|Twin-turbine air conditioning system
    FR3062972A1|2018-08-17|DEVICE FOR GENERATING AUXILIARY ELECTRICITY AND TURBOMACHINE COMPRISING SUCH A DEVICE
    同族专利:
    公开号 | 公开日
    EP3194270B1|2018-08-29|
    FR3025497B1|2016-09-30|
    WO2016034830A1|2016-03-10|
    US10053220B2|2018-08-21|
    US20170355466A1|2017-12-14|
    EP3194270A1|2017-07-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20070113579A1|2004-08-25|2007-05-24|Claeys Henry M|Low energy electric air cycle with portal shroud cabin air compressor|
    US7797962B2|2005-08-08|2010-09-21|Liebherr-Aerospace Lindenberg Gmbh|Method of operating an aircraft system|
    EP2592001A2|2011-11-11|2013-05-15|Hamilton Sundstrand Corporation|Turbo air compressor with pressure recovery|
    KR19990075384A|1998-03-20|1999-10-15|이헌석|Compact Turbo Compressor|
    US6725643B1|2001-06-19|2004-04-27|Marius Paul|High efficiency gas turbine power generator systems|
    US6666039B2|2001-07-05|2003-12-23|Shimadzu Corporation|Aircraft air conditioner|
    US6526775B1|2001-09-14|2003-03-04|The Boeing Company|Electric air conditioning system for an aircraft|
    DE10350541A1|2003-10-29|2005-06-16|Liebherr-Aerospace Lindenberg Gmbh|Air conditioning system and method for treating air for air conditioning of a room|
    US7669418B2|2004-12-17|2010-03-02|Hitachi, Ltd.|Heat energy supply system and method, and reconstruction method of the system|
    US7607318B2|2006-05-25|2009-10-27|Honeywell International Inc.|Integrated environmental control and auxiliary power system for an aircraft|
    US7958873B2|2008-05-12|2011-06-14|Cummins Inc.|Open loop Brayton cycle for EGR cooling|
    US8323000B2|2008-06-23|2012-12-04|Compressor Controls Corp.|Compressor-driver power limiting in consideration of antisurge control|
    US8938962B2|2012-01-31|2015-01-27|Caterpillar Inc.|Exhaust system|US20170268837A1|2016-03-16|2017-09-21|Hamilton Sundstrand Corporation|Pack-and-a-half architecture for environmental control systems|
    FR3065518B1|2017-04-20|2019-07-05|Liebherr-Aerospace Toulouse Sas|METHOD AND DEVICE FOR THERMALLY CONTROLLING A PLURALITY OF CABINS OF A VEHICLE|
    US10507928B2|2017-06-16|2019-12-17|Honeywell International Inc.|High efficiency electrically driven environmental control system|
    US10703491B2|2017-11-28|2020-07-07|Hamilton Sunstrand Corporation|Aircraft cabin air monitor|
    DE102017128338A1|2017-11-29|2019-05-29|Airbus Operations Gmbh|Air conditioning system for an aircraft|
    FR3088994B1|2018-11-28|2020-12-25|Liebherr Aerospace Toulouse Sas|HEAT EXCHANGER AND FLUID COOLING SYSTEM INCLUDING SUCH A HEAT EXCHANGER|
    WO2020219747A2|2019-04-23|2020-10-29|Joby Aero, Inc.|Battery thermal management system and method|
    US11230384B2|2019-04-23|2022-01-25|Joby Aero, Inc.|Vehicle cabin thermal management system and method|
    FR3097529B1|2019-06-21|2021-06-18|Liebherr Aerospace Toulouse Sas|ELECTRIC AIR CONDITIONING SYSTEM FOR AN AIRCRAFT CABIN INCLUDING A MOTORCOMPRESSOR AND AN AIR CYCLE TURBOMACHINE|
    法律状态:
    2015-09-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-11| PLSC| Publication of the preliminary search report|Effective date: 20160311 |
    2016-09-23| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-25| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-25| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-24| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458359A|FR3025497B1|2014-09-05|2014-09-05|AIR CONDITIONING SYSTEM FOR "MORE ELECTRIC" AIRCRAFT|FR1458359A| FR3025497B1|2014-09-05|2014-09-05|AIR CONDITIONING SYSTEM FOR "MORE ELECTRIC" AIRCRAFT|
    US15/507,099| US10053220B2|2014-09-05|2015-09-04|Air conditioning system for a “more electric” airplane|
    PCT/FR2015/052358| WO2016034830A1|2014-09-05|2015-09-04|Air conditioning system for a "more electric" airplane|
    EP15766923.5A| EP3194270B1|2014-09-05|2015-09-04|Air conditioning system for a "more electric" airplane|
    [返回顶部]