Air conditioning method and system for aircraft

Abstract

Air conditioning system for the pressurized cabin of an aircraft, said system (1) being characterized in that it comprises an air withdrawal module (3) configured for withdrawing ambient air from outside the aircraft, an air compression module (5) configured for compressing the withdrawn air flow (F1) and an air cooling module (10) comprising means (15) for storing at least one coolant configured for cooling the compressed air flow (F2, F3).

Claims

1. Air conditioning system for a pressurised cabin of an aircraft including at least one main engine, said system comprising: an air withdrawal module including one or more ambient outside air inlets, said withdrawal module withdrawing air which is not withdrawn from the at least one main engine and which is configured for withdrawing one single open ambient air flow from outside the aircraft through said one or more ambient outside air inlets which is formed, either by a dynamic air inlet or by a controllable valve, an air compression module independent from the at least one main engine configured for compressing the single open ambient air flow withdrawn from outside the aircraft to create a single compressed air flow, and an air cooling module configured for cooling the single compressed air flow by means of a cryogenic fluid, the air cooling module comprising a condenser for condensing water from the single open ambient air flow, a water extractor for extracting said water, a cooler for cooling said single open ambient air flow emitted by the water extractor and a tank for cryogenic fluid, by means of which the water from the single open ambient air flow is condensed in the condenser and the single open ambient air flow emitted by the water extractor is cooled in the cooler, wherein the single compressed air flow being either directed to the air cooling module or to a thermal exchange module by means of an air flow orientation module, and wherein the cooling module is configured for delivering a gaseous fluid produced by a heat exchange between the single compressed air flow and a cryogenic fluid, the gaseous fluid being routed towards the thermal exchange module for supply to a turbine.

2. System according to claim 1, wherein the cooling module is contained within a housing.

3. System according to claim 1, in which the thermal exchange module arranged between the air compression module and the cooling module and configured for cooling the single compressed air flow received from the air compression module by means of the flow of gaseous fluid delivered by the cooling module, and for routing, on the one hand, the single compressed air flow thus cooled towards the cooling module and, on the other hand, the flow of gaseous fluid towards a heating module.

4. System according to claim 1, in which the air flow orientation module arranged between the compression module and the cooling module and configured for orienting the single open ambient air flow compressed by the air compression module towards the air cooling module when a temperature of the single compressed air flow is greater than a temperature required at the inlet of an air conditioning module of the cabin, or towards a heating module when the temperature of the single compressed air flow is lower than the temperature required at the inlet of the air conditioning module of the cabin.

5. System according to claim 1, said system comprising a heating module configured for receiving, from the thermal exchange module, a flow of gaseous fluid and for routing said flow of gaseous fluid towards a turbine, and for receiving, from the air orientation module, the single compressed air flow to be reheated and for routing said flow of gaseous fluid towards an air conditioning module of the cabin of the aircraft.

6. Aircraft comprising the air conditioning system according to claim 1.

7. System according to claim 1, wherein the air compression module is configured for compressing the single open ambient air flow at a low compression rate between 3 or 4.

Description

(1) Further features and advantages of the invention will become apparent in the following description, made with reference to the accompanying figures which are given by way of non-limiting example and in which similar objects are provided with identical reference signs:

(2) FIG. 1 is a diagram of the air conditioning system according to the invention;

(3) FIG. 2 is a diagram of the cooling module of the system from FIG. 1;

(4) FIG. 3 shows the air conditioning method according to the invention.

DETAILED DESCRIPTION

(5) In an aircraft, the air conditioning system makes it possible to supply the pressurised cabin with air from the outside.

Description of the System According to the Invention

(6) The embodiment of the air conditioning system 1 according to the invention shown in FIG. 1 comprises an air withdrawal module 3, an air compression module 5, an air orientation module 7, a thermal exchange module 9, a cooling module 10, a thermal recovery module 20, a turbine 30, and an air conditioning module 40 of the pressurised cabin of the aircraft.

(7) Air Withdrawal Module 3

(8) The air withdrawal module is configured for withdrawing ambient air from outside the aircraft. The air withdrawal module 3 comprises one or more ambient outside air inlets, preferably a single air inlet, for example of the dynamic air inlet type. An air inlet is said to be dynamic (as opposed to a static air inlet) when it is capable of transforming kinetic energy from the captured air into pressure (shut-off pressure or dynamic pressure). A dynamic air inlet of this kind may be that of an auxiliary power unit (APU) of the aircraft. In an alternative embodiment, the air withdrawal module may be formed of one or more controllable air withdrawal valves.

(9) Air Compression Module 5

(10) The air compression module 5 comprises at least one compressor, which may for example be the load compressor of an auxiliary power unit of the aircraft. A unit of this kind usually comprises a load compressor 5 and a turbine engine comprising a motor or a generator 35 and a turbine 30. The load compressor 5 is configured for receiving the air flow F1 withdrawn by the withdrawal module 3, compressing said air flow and routing the compressed air flow F2 to the air orientation module 7.

(11) Air Orientation Module 7

(12) The air orientation module 7, for example a two-way valve, is configured for orienting the compressed air flow F2 towards the thermal exchange module 9 or towards the thermal recovery module 20. The air orientation module 7 comprises means for measuring the temperature of the compressed air flow F2 coming from the air compression module 5 and means for comparing the measured value with a reference value corresponding to a level required at the inlet of the cabin air conditioning module 40. The air orientation module 7 is thus configured for orienting the compressed air flow F2 towards the thermal exchange module 9 in order to then cool said air flow when the measured temperature of the compressed air is greater than that of the level required at the inlet of the air conditioning module 40. The air orientation module 7 is also configured for orienting the compressed air flow towards the thermal recovery module 20 in order to reheat said air flow when the measured temperature of the compressed air is lower than that of the level required at the inlet of the air conditioning module 40.

(13) Thermal Exchange Module 9

(14) The thermal exchange module 9 comprises at least one heat exchanger configured for permitting heat exchange between the compressed air flow F2 received from the air orientation module 7 and a flow of gaseous fluid F5 coming from the cooling module 10.

(15) Cooling Module 10

(16) The cooling module 10 is configured for receiving the air flow F3 coming from the air orientation module 7 and having passed through the thermal exchange module 9, and for cooling said received flow F3. As shown in FIG. 2, the cooling module comprises a condenser 12, a water extractor 13, a cooler 14, a tank of cryogenic fluid 15, for example liquid nitrogen pressurised to 10 bar, a first regulation valve 16 arranged between the cryogenic fluid tank 15 and the condenser 12, and a second regulation valve 17 arranged between the cryogenic fluid tank 15 and the cooler 14. The condenser 12 is configured for receiving an air flow to be cooled, for example a compressed air flow which is possibly humid, at a temperature of up to 100 C. at cabin pressure, for example approximately 0.8 bar. The condenser 12 is also configured for condensing the water vapour contained in the received compressed air flow while avoiding the icing thereof by maintaining a positive temperature at the outlet. The water extractor 13 is configured for extracting water from the air flow, condensed by the condenser 12, the water flow F8 of which may then be, for example, eliminated or injected into a water system of the aircraft. The cooler 14 is configured for cooling the dry air flow received from the water extractor 13 by means of cryogenic fluid received from the tank 15 via the second regulation valve 17, and for routing the obtained cold, dry air flow F4 towards the cabin air conditioning module 40. The liquid cryogenic fluid stored in the tank is thus used by both the condenser 12 and the cooler 14. The coolant, passed in gaseous form following the heat exchanges carried out in the condenser 12 and the cooler 14, is recycled by being routed towards the thermal exchange module 9 in order to cool the compressed air flow F2 passing through the thermal exchange module 9 and coming from the air orientation module 7.

(17) Heating Module 20

(18) The heating module 20 may be in the form of a thermal recuperator, arranged for example in the exhaust of the auxiliary power unit (APU). The heating module 20 is configured for, in a first mode of functioning, heating the air flow F2 received from the air orientation module 7 and then routing said air flow towards the cabin air conditioning module 40 and for, in a second mode of functioning, heating the flow of gaseous coolant F5 received from the thermal exchange module 9 and sending said flow towards the turbine 30. A route by-passing said heating module may be provided for regulating the thermal energy for heating the air flow F2.

(19) Turbine 30

(20) The turbine 30 is configured for receiving a flow of gaseous fluid from the heating module 20. The mechanical energy produced by the turbine 30 from the received flow of gaseous fluid may, for example, be injected into the gearbox of the auxiliary power unit (APU) or used for driving an alternator, or for any other use which may be more appropriate. The exiting gaseous flow F7 may again be used for cooling the engine bay of the aircraft and/or for making the atmosphere inert if said fluid is nitrogen gas for example.

(21) Air Conditioning Module of the Pressurised Cabin of the Aircraft

(22) The air conditioning module 40 comprises a mixer (not shown) configured for receiving the cooled air flow F4 from the cooling module 10 and for mixing said air flow with air from the cabin in order to provide the cabin with an air flow at the desired control temperature.

(23) The system according to the invention may also comprise means for regulating the pressure of the cabin (not shown) and control means configured for controlling one or all of the modules of the system (air withdrawal module, air compression module, air orientation module, cooling module, air conditioning heating turbine, etc.).

Use of the System According to the Invention

(24) In a first step E1, the air withdrawal module 3 withdraws ambient outside air and routes the flow of withdrawn ambient air F1 towards the air compression module 5.

(25) In a step E2, the air compression module 5 compresses the withdrawn air F1 and sends the compressed air flow F2 towards the air orientation module F7.

(26) In a step E3, the air orientation module 7 determines whether the temperature of the compressed air flow F2 is greater or lower than a reference value associated with the level required at the inlet of the air conditioning module 40.

(27) When the temperature of the compressed air flow is greater than the reference value, the air orientation module 7 routes, in a step E4, the compressed air flow F2 to be cooled towards the thermal exchange module 9. The compressed air flow F2 then passes through the thermal exchange module 9, in which it undergoes a first cooling, during a step E5, by a gaseous fluid F5 coming from the cooling module 10. The compressed air flow F3 is then routed to the cooling module 10, in which it undergoes a second cooling during a step E6.

(28) More specifically, the compressed air flow F3 passes through the condenser 12 in a step E61, during which the water vapour which may be present in the air flow is condensed. The condenser 12 uses the cryogenic fluid received, via the first valve 16, from the cryogenic fluid tank 15 in order to reduce the temperature of the air flow to a temperature which is just positive, for example 2 C., in order to allow condensation of the water vapour without icing. The gaseous fluid F5 produced by the heat exchange between the air flow and the cryogenic fluid is then routed towards the thermal exchange module 9.

(29) The water is then extracted from the air flow, in a step E62, by the water extractor 13, and then the air flow is routed to the cooler 14 which then uses, in a step E63, the cryogenic fluid received via the second valve 17, in order to reduce the temperature of the dry air flow to the level of the temperature required at the inlet of the air conditioning module 40, for example 15 C. The gaseous fluid produced by the heat exchange between the air flow and the cryogenic fluid is also routed towards the thermal exchange module 9.

(30) The cold, dry air flow F4 is then routed, in a step E7, to the cabin air conditioning module 40. The temperature desired in the cabin can then be obtained by means of the mixer of the air conditioning module 40. Moreover, the means for regulating the cabin pressure make it possible to keep the cabin pressurised, for example at 0.8 bar.

(31) The gaseous fluid F5 emitted by the heat exchanges in the condenser 12 and in the cooler 14 is routed via a feedback loop, during a step E8, to the thermal exchange module 9 where it is used for carrying out a first cooling of the compressed air flow F2 coming from the air orientation module 7.

(32) Once the heat exchange has been carried out in the thermal exchange module 9, the flow of gaseous fluid is routed to the heating module 20, which increases the temperature thereof, in a step E9, prior to sending said fluid towards the turbine 30 of the APU in a step E10. The turbine 30 can then use the flow of gaseous fluid F6 in order to, for example, supply a generator and produce electricity.

(33) When the temperature of the flow of gaseous fluid F7 is lower than a reference value, for example one-thirtieth of a degree Celsius, the flow can be used to cool the engine bay of the aircraft and/or to make the atmosphere inert, in s step E11.

(34) When the temperature of the compressed air flow F2 is lower than the reference value, the air orientation module 7 routes, in a step E12, the compressed air flow F2 to be heated towards the heating module 20.

(35) The heating module 20 then increases the temperature of the air flow during a step E13 and then routes said air flow towards the cabin air conditioning module 40 during a step E14. The temperature desired in the cabin can then be obtained using the mixer of the air conditioning unit 40.

(36) It will be appreciated that, in a simplified embodiment of the system according to the invention, the thermal exchange module 9 may be omitted, and the compressed air flow F2 may then be routed directly from the air orientation module 7 to the cooling module 10.

(37) The system according to the invention thus makes it possible to compress an air flow withdrawn from the ambient air outside the aircraft to a value close to that of the pressure required in the cabin, for example at a compression rate of 3 or 4, which therefore does not require much energy. The cooling module then makes it possible to cool the flow in order to reduce the temperature thereof to the level required at the inlet of the cabin air conditioning module.