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公开(公告)号：US20230138228A1
公开(公告)日：2023-05-04
申请号：US17979023
申请日：2022-11-02
Applicant: Airbus Operations SAS
Inventor： Arnaud BOURHIS , Florian RAVISE , Maxime ZEBIAN
IPC: F02C7/045
Abstract: A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.
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公开(公告)号：US20210231057A1
公开(公告)日：2021-07-29
申请号：US17158982
申请日：2021-01-26
Applicant: Airbus Operations SAS
Inventor： Thomas LIVEBARDON , Maxime ZEBIAN
Abstract: A turbomachine for an aircraft, comprising a thermoacoustic system associated with a fluid circuit that serves to supply the motor of the turbomachine with fluid. The thermoacoustic system comprises an exchanger which is connected to the fluid circuit and in which there flows a fluid that is to be cooled, an acoustic attenuation structure which is distinct from the exchanger and which forms all or part of a wall of the fan duct, and at least one heat-duct tube comprising a portion that is entirely received in the acoustic structure and a portion with an end that is received in the exchanger, and a single curved elbow with a non-zero angle between the two portions.
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公开(公告)号：US20220267021A1
公开(公告)日：2022-08-25
申请号：US17678176
申请日：2022-02-23
Applicant: Airbus Operations SAS
Inventor： Maxime ZEBIAN , Davy BOURGALET
Abstract: An aircraft having an engine, a dihydrogen tank, devices to be heated, a first air intake for taking in air at a low pressure or at an intermediate pressure, a second air intake for taking in air at a high pressure, a first heat exchanger, a first pipe which passes through the first heat exchanger and feeds the devices to be heated. Upstream of the first heat exchanger, the first pipe is divided into two sub-pipes connected respectively to the first air intake and the second air intake, and a fuel pipe that is connected between the tank and the combustion chamber and passes through the first heat exchanger. The use of heat exchangers on the dihydrogen pipe allows a regulation of the temperature of the devices to be heated and of the engine and to increase the temperature of the dihydrogen before its combustion.
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公开(公告)号：US20210261267A1
公开(公告)日：2021-08-26
申请号：US17181585
申请日：2021-02-22
Applicant: Airbus Operations SAS
Inventor： Yannick SOMMERER , Maxime ZEBIAN
Abstract: A propulsion assembly with a primary duct and a secondary duct, an outer fairing delimiting an outer compartment with an inlet opening, an inner fairing delimiting an inner compartment with an air exhaust aperture, a suction system having an inlet, an outlet and mobile elements that draw the air in via the inlet and deliver the air via the outlet, a drive that drives the mobile elements, a transfer pipe connected to the outlet, a distribution pipe disposed in the inner compartment, connected to the transfer pipe and having nozzles, a supply pipe that opens into the outer compartment and is connected to the inlet, and a regulator that regulates the flow rate of air in the suction system. The outside air is then driven by the suction system and passes through the two compartments in a forced manner.
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公开(公告)号：US20220290614A1
公开(公告)日：2022-09-15
申请号：US17686759
申请日：2022-03-04
Applicant: Airbus Operations SAS
Inventor： Maxime ZEBIAN , Davy BOURGALET
Abstract: An aircraft having an engine, a tank, devices to be heated, air intakes, a heat exchanger, a pipe connecting the air intakes and the devices to be heated by passing through the heat exchanger, a fuel pipe connected between the tank and the combustion chamber of the engine, and an air pipe which feeds the heat exchanger from the fan duct. The aircraft has an additional heat exchanger installed on the pipe between the heat exchanger and the air intakes, and a diversion pipe that passes through the additional heat exchanger and is connected at each end to the fuel pipe. The use of the fuel to cool the air makes it possible to use a smaller and therefore less bulky heat exchanger.
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Patent Agency Ranking
公开(公告)号：US20190120082A1
公开(公告)日：2019-04-25
申请号：US16162710
申请日：2018-10-17
Applicant: Airbus Operations SAS
Inventor： Maxime ZEBIAN , Ali KAPEKOV
IPC: F01D25/14
CPC classification number: F01D25/14 , F01D17/085 , F01D25/12 , F02C7/18 , F05D2260/20 , F05D2260/608 , F05D2270/42 , F05D2300/505
Abstract: A turbomachine of bypass type comprising a nacelle defining a fan duct with an interduct. The turbomachine comprises at least one compartment created in the thickness of the interduct or of the nacelle. The compartment is separated from the fan duct by a cold wall and comprises at least one heat-sensitive element. The compartment further is equipped with a ventilation assembly comprising at least one ventilation opening made in the cold wall in order, in use, to cause air from the fan duct to enter the compartment. Each ventilation opening comprises a passive-opening system arranged in the compartment, the system comprising a flap able to move between an open position in which the flap uncovers the opening and a closing-off position in which the flap closes off the opening, and a passive-actuation device of the flap for moving the flap between the two positions.
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公开(公告)号：US20220231311A1
公开(公告)日：2022-07-21
申请号：US17574917
申请日：2022-01-13
Applicant: Airbus Operations SAS
Inventor： Maxime ZEBIAN
IPC: H01M8/04007 , B64C1/06 , B64C3/34
Abstract: An aircraft comprising a structure comprising a leakproof tank delimited by walls, of which at least one is in contact with the air outside the aircraft, and filled partly with a two-phase heat-transfer fluid, a fuel cell that is passed through by a heat-transfer fluid, and a line which takes the heat-transfer fluid at an output of the fuel cell and which reintroduces this heat-transfer fluid at an input of the fuel cell. The line passes through the leakproof tank immersed in the heat-transfer fluid in liquid phase.
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公开(公告)号：US20220135236A1
公开(公告)日：2022-05-05
申请号：US17512188
申请日：2021-10-27
Applicant: Airbus Operations SAS
Inventor： Antoine ABELE , Maxime ZEBIAN
Abstract: An aircraft having an engine, a cabin, an air conditioning system collecting the hot air from the engine, so as to treat the hot air, regulate a temperature of the hot air and send the hot air towards the cabin via a main line, an air line channeling the air leaving the cabin, and an arrangement for cooling the engine using the air thus drawn off by the air line. By drawing off the air at the outlet of the cabin, the performance of the engine is improved and the fuel consumption is reduced.
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9.发明申请公开(公告)号：US20210270191A1
公开(公告)日：2021-09-02
申请号：US17185364
申请日：2021-02-25
Applicant: Airbus Operations SAS
Inventor： Maxime ZEBIAN
Abstract: A regulation system to regulate the flow rate of a hot air duct which comprises a shutter, an upstream air intake, a downstream air intake, a regulator and an actuator of the shutter with a first inlet connected to an outlet of the regulator and a cooling system comprising an outer radiator, a housing and a heat pipe housed in the housing and discharging the heat between the housing and the outer radiator, wherein the air streams coming from the upstream air intake and from the downstream air intake pass through the housing. Such a regulation system allows a better discharging of the heat by the action of the heat pipes.
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公开(公告)号：US20210254911A1
公开(公告)日：2021-08-19
申请号：US17173425
申请日：2021-02-11
Applicant: Airbus Operations SAS
Inventor： Maxime ZEBIAN
IPC: F28F27/02
Abstract: An exchanger system comprising two heat exchangers, a bypass line which extends between an inlet and an outlet, a line connected between the bypass line and a first orifice of each heat exchanger, a return line connected to two second orifices of the two heat exchangers and to the bypass line, three valves, and a controller which commands each valve alternately to open or to close. With such an arrangement, the intensities of the pressure peaks due to plugs are limited by distribution of the flow of the heat-transfer fluid in two parallel lines.
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