Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
  • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
  • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
  • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
  • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
  • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/06—Arrangements of bearings; Lubricating
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
  • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
  • F02K3/105—Heating the by-pass flow
  • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
  • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
  • B64D2013/0603—Environmental Control Systems
  • B64D2013/064—Environmental Control Systems comprising more than one system, e.g. dual systems
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/20—Heat transfer, e.g. cooling
  • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/50—On board measures aiming to increase energy efficiency
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the invention relates to an air conditioning system comprising a cooling system.
• the invention relates to an air conditioning system for an aircraft cabin.
• a conventional oil cooling system of an aircraft turbojet engine comprises finned heat exchangers cooled for example by means of:
• fan air refers to the air passing through the engine. In a double-flow turbojet engine, it is made up of the primary flow and the secondary.
• the hot power transmitted to the oil is much higher (typically 3 times higher) than in a conventional aircraft engine, which requires oversizing the oil cooling system.
• the air conditioning system is supplied by air from a compressor, called pressurized air, which must be cooled to reach a temperature suitable for the supply of air to the cabin of the aircraft. aircraft.
• pressurized air a compressor
• This need for cooling is all the more important as the pressurized air is at a high compression ratio and therefore at a high temperature. The heat of this pressurized air is lost during cooling.
• the invention aims to provide an air conditioning system providing thermal management of engine oil and pressurized air.
• the invention aims in particular to provide, in at least one embodiment of the invention, an air conditioning system which does not require bleeding of air from the air flow of the engine.
• the invention also aims to provide, in at least one embodiment of the invention, an air conditioning system having a small footprint.
• the invention also aims to provide, in at least one embodiment of the invention, an air conditioning system allowing energy optimization by recovery and transfer of heat during heat exchanges.
• the invention also aims to provide, in at least one embodiment of the invention, an air conditioning system allowing engine oil to be preheated before takeoff, in cold conditions.
• the invention relates to an air conditioning system of an aircraft cabin, comprising a thermal management system supplied with air, called pressurized air, by at least one compressor of the aircraft, and supplied with non-pressurized flow air coming from at least one engine of the aircraft, and characterized in that the thermal management system comprises:
• At least one pressurized air / oil heat exchanger configured to provide heat exchanges between a pressurized air flow and a first oil circuit making it possible to transfer heat from the pressurized air to the oil of the first oil circuit
• At least one flow oil / air heat exchanger configured to provide heat exchanges between a second oil circuit and the flow air making it possible to transfer heat from said second oil circuit to the flow air ,
• An air conditioning system therefore makes it possible, thanks to its thermal management system, to effect a double transfer of heat between different air flows of the aircraft, while cooling the oil. engine.
• the pressurized air is cooled as it passes through the pressurized air / oil heat exchanger.
• the pressurized air therefore forms a hot pass of the exchanger and the oil forms a cold pass of the exchanger.
• the pressurized air thus cooled is processed by the rest of the air conditioning system.
• the pressurized air is intended in particular to supply an air conditioning unit of the air conditioning system making it possible to adjust the temperature, pressure and humidity of the pressurized air so as to obtain conditioned air. which can be sent to the cabin of the aircraft.
• this cooling of the pressurized air is generally carried out by taking off air from the engine.
• the conditioning system according to the invention therefore makes it possible to eliminate this levy in order to avoid loss of engine performance. Replacing this air bleed by an oil exchanger also reduces the bulk, in particular by removing the conduits leading the flow air taken from the pressurized air / flow air exchanger in the prior art.
• the pressurized air is supplied for example by the compressor of one or more engines of the aircraft, or else by a compressor dedicated to the air conditioning system, motorized or driven by a turbine and drawing air from outside the aircraft.
• the engine oil is cooled as it passes through the flow oil / air heat exchanger.
• the oil therefore forms a hot pass of the exchanger and the flow air forms a cold pass of the exchanger.
• This makes it possible, on the one hand, to cool the engine oil, which is necessary for the proper functioning of the engine during phases of flight, and on the other hand to heat the engine flow air, which increases the performance of the engine (especially increased thrust).
• the air conditioning system thus performs an indirect heat transfer between the pressurized air and the flow air, via the engine oil. This allows an overall energy optimization of the air conditioning system.
• Engine oil cooling is no longer seen as a constraint reducing engine performance but fits perfectly into an overall system in which heat is transferred from pressurized air where excessive heat is reduced to dry air. 'flow where extra heat is useful.
• engine oil cooling is generally sized for maximum cooling capacity that exceeds conventional operating conditions.
• the cooling margin resulting from this difference can therefore be used for cooling the pressurized air intended to supply an air conditioning unit of the air conditioning system.
• the thermal management performed by the thermal management system consists of therefore both in cooling the pressurized air, heating the oil from the first oil circuit (useful during preheating), cooling the oil from the second oil circuit and heating the oil. flow air.
• Engine oil in the broad sense designates for example the lubricating oil of the gearbox (Power Gear Box or PGB in English), or the lubricating oil of the accessory gearbox (Accessory Gear Box or AGB in English), or the cooling oil of the Integrated Drive Generator (IDG), or the cooling oil of the electric generator, or any other cooling, lubricating oil, etc. that can be used by an engine or generator type component of the aircraft for cooling or lubricating this component, in particular the lubrication of the bearings of this component. Oil is generally shared among these components but not necessarily, as some components may have a dedicated oil circuit.
• the oil is an engine oil and the thermal management system comprises a lubrication passage configured to lubricate and cool the bearings of the engine of the aircraft using the engine oil, said passage lubrication being integrated in the first oil circuit or the second oil circuit.
• the thermal management system uses engine oil and is fully integrated into the already existing part of the circuit formed by the lubrication passage.
• the thermal management system therefore does not require an additional circuit but consists of a diversion of the existing engine oil circuit, both to improve the cooling of this engine oil and to use the heat transport capacity of this oil.
• the oil / air flow heat exchanger is a heat exchanger arranged in the engine of the aircraft and configured to have a heat exchange surface in direct contact with the air flow. flow through the motor.
• Such an exchanger also called a skin exchanger, has a small footprint and reduces the disturbances of the flow air by not impacting the flow of flow and not taking a sample, thus not degrading engine performance.
• the flow oil / air heat exchanger is arranged in a casing of the engine of the aircraft.
• the casing refers to the envelope around the engine, in which the flow of exhaust air flows.
• the casing guides the secondary air flow around the central part made up of a compressor, a combustion chamber and a turbine, and in which the primary flow flows.
• the flow oil / air heat exchanger is arranged at a flow air inlet in the crankcase of the engine of the aircraft.
• crankcase air inlet is a privileged position to maximize heat exchange and reduce flow air disturbances.
• the transmission of heat through the oil allows protection against frost of the engine inlet, which is one of the areas most subject to the formation of frost which can be dangerous for the proper functioning of the engine. .
• the flow oil / air heat exchanger is arranged in the casing after a fan of the engine of the aircraft.
• heat exchange is maximized because the engine fan creates turbulence which improves airflow.
• the flow oil / air heat exchanger is composed of a multitude of elements arranged at several locations on the housing.
• the pressurized air / oil heat exchanger and the oil / flow air heat exchanger are arranged in series.
• the first oil circuit, the second oil circuit and the link circuit can thus form a single circuit.
• the air heat exchanger pressurized / oil and oil / air flow heat exchanger are arranged in parallel.
• the connecting circuit can for example be an oil tank from which the oil leaves to enter the first and the second circuit, and in which the oil from the first and second circuit is returned after passing through the respective exchangers. .
• the thermal management system comprises a pressurized air / oil heat exchanger bypass circuit, configured to be controlled by a pressurized air temperature control module.
• bypass circuit makes it possible to control the temperature of the pressurized air according to the needs of the conditioning system, in particular according to the desired temperature at the pressurized air inlet and / or the desired temperature in the cabin. the aircraft.
• the bypass can either be a bypass of the pressurized air (the latter therefore does not pass through the pressurized air / oil heat exchanger) or bypassing the oil (the latter therefore does not pass into the heat exchanger. pressurized air / oil heat), or both.
• the invention also relates to an aircraft comprising at least one engine, at least one compressor and an air conditioning system according to the invention.
• the invention also relates to an air conditioning system and an aircraft, characterized in combination by all or part of the characteristics mentioned above or below.
• FIG. 1 is a schematic view of an air conditioning system according to a first embodiment of the invention.
• FIG. 2 is a schematic view of an air conditioning system according to a second embodiment of the invention.
• Figures 1 and 2 illustrate an air conditioning system 10 according to a first and a second embodiment of the invention.
• the air conditioning system 10 provides for the refrigeration and conditioning of the air for a cabin 100 of an aircraft during its flight.
• the aircraft includes at least one engine 200.
• the engine 200 is of the bypass turbojet type, comprising a casing 202 surrounding a turbomachine 204 conventionally comprising a compressor, a combustion chamber and a turbine (not shown).
• the turbomachine 204 generates a primary flow 206.
• a fan 210 connected to the turbomachine generates a secondary flow between the turbomachine 204 and the casing 202.
• the primary flow 206 and the secondary flow 208 are directed in the direction of the arrows representing them and constitute an engine flow air.
• the turbomachine 204 is supplied by at least one oil circuit, allowing it to operate correctly, in particular by allowing the lubrication and cooling of the bearings of the turbomachine 204 of the engine. This oil heats up while the engine is running and must be cooled.
• the air conditioning system 10 is supplied with air, said air 12 pressurized by a compressor 14.
• the compressor 14 can be part of the conditioning system and be mainly dedicated to the supply of air conditioning.
• the pressurized air 12, or else form part of the engine 200 of the aircraft, in particular may be the compressor of the turbomachine 204.
• the compressor is supplied with air 16 taken off.
• the pressurized air 12 is treated by an air conditioning unit 18 making it possible to adjust the temperature, pressure and humidity of the pressurized air 12 so as to obtain conditioned air which can be sent to the room. cabin aircraft.
• the air conditioning unit 18 can for example comprise a water extraction loop to reduce the humidity of the air, at least one turbine to reduce its pressure, at least one exchanger to control its temperature.
• the air conditioning system 10 includes a thermal management system for reducing the temperature of the pressurized air 12.
• the thermal management system comprises at least one pressurized air / oil heat exchanger configured to provide heat exchanges between the pressurized air flow and an oil circuit making it possible to transfer heat from the pressurized air to the oil.
• the oil comes from the turbomachine 204 and circulates in a first oil circuit and enters the pressurized air / oil heat exchanger 20 through an oil inlet 20a and exits through an oil outlet 20b.
• the pressurized air 12 enters the pressurized air / oil heat exchanger 20 through a pressurized air inlet 20c and exits through a pressurized air outlet 20b.
• the pressurized air 12 is thus cooled as it passes through the exchanger and transmits part of its heat to the oil.
• the thermal management system is also configured to cool the oil, and thus comprises at least one oil / flow air heat exchanger configured to provide heat exchanges between the oil and the flow air making it possible to transfer the heat. heat from oil to flowing air.
• the flow oil / air heat exchanger is composed of a plurality of skin exchangers, four of which are visible here: two skin exchangers 22a, 22b are located at level d an engine air inlet 212, at one end of the casing 202. These exchangers can thus have a defrost function which prevents the formation of frost at the engine air inlet, an area usually sensitive to the risk of frost formation. Two skin exchangers 22c, 22d are located on the housing 202 after the blower 210.
• FIG. 1 shows a first embodiment of the invention, in which the pressurized air / oil heat exchanger 20 and the skin exchangers 22a, 22b, 22c, 22d forming the oil / flow air heat exchanger are arranged in series: the first oil circuit and the second oil circuit form a single circuit 24.
• the oil leaving the pressurized air / oil heat exchanger 20 through the outlet 20b is then guided to a skin exchanger, in the same oil circuit.
• the heat recovered by the oil in the pressurized air / oil heat exchanger 20 is transferred directly to the flow air to heat the latter (cooling the oil as it passes).
• bypass circuits can be set up, for example via a bypass valve 21a to prevent the oil from passing into the pressurized air exchanger 20. / oil, or via a bypass valve 21b to prevent pressurized air 12 from passing into pressurized air / oil exchanger 20, or both as shown here.
• FIG. 2 shows a second embodiment of the invention, in which the pressurized air / oil heat exchanger 20 and the skin exchangers 22a, 22b, 22c, 22d forming the oil / flow air heat exchanger are arranged in parallel.
• the first oil circuit 26 and the second oil circuit 28 are separate but connected by a connecting circuit 30, which may for example be an oil tank in which the oil from each circuit mixes and balances its temperature: the oil coming from the first circuit is heated in its passage by the pressurized air / oil heat exchanger 20 and the oil coming from the second circuit is cooled by the oil / flow air heat exchanger, and mixes in the oil tank, the temperature leaving the tank to the exchangers is the same for both circuits.
• a connecting circuit 30 may for example be an oil tank in which the oil from each circuit mixes and balances its temperature: the oil coming from the first circuit is heated in its passage by the pressurized air / oil heat exchanger 20 and the oil coming from the second circuit is cooled by the oil / flow air heat exchanger, and mixes in the oil tank, the temperature leaving the tank to the exchangers is the same for both circuits.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Health & Medical Sciences (AREA)
• General Health & Medical Sciences (AREA)
• Pulmonology (AREA)
• Aviation & Aerospace Engineering (AREA)
• Lubrication Of Internal Combustion Engines (AREA)
• Other Air-Conditioning Systems (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=67107843

Family Applications (1)

Country Status (4)

Families Citing this family (3)

Family Cites Families (5)

• 2019
  • 2019-03-11 FR FR1902465A patent/FR3093766B1/fr active Active
• 2020
  • 2020-03-10 WO PCT/FR2020/050492 patent/WO2020183104A1/fr unknown
  • 2020-03-10 EP EP20725869.0A patent/EP3938639A1/de active Pending
  • 2020-03-10 US US17/438,924 patent/US20220185485A1/en active Pending

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