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    Turbomachine fitted with a thermo-acoustic system
    1.
    发明授权
    Turbomachine fitted with a thermo-acoustic system 有权

    公开(公告)号：US11293348B2

    公开(公告)日：2022-04-05

    申请号：US16574946

    申请日：2019-09-18

    Applicant: Airbus Operations SAS

    Inventor： Maxime Zebian

    IPC: F02C7/14 ,  F02C7/24 ,  F02K1/82 ,  F02K3/06

    Abstract: A turbomachine for an aircraft comprising a thermo-acoustic system associated with a fluid circuit allowing the turbomachine engine to be supplied with fluid, the thermo-acoustic system comprising an exchanger connected to the fluid circuit and through which the fluid that is to be cooled passes, an acoustic noise-attenuation structure forming, in full or in part, a wall of the duct of a fan duct, the structure being situated some distance from the exchanger, and a pulsating heat pipe comprising a tube extending between the exchanger and the acoustic noise-attenuation structure, the tube having a serpentine form with a plurality of elbows bent over at 180° housed alternately in the exchanger and the structure.

    Aircraft turbomachine comprising a compartment equipped with a ventilation assembly
    3.
    发明授权
    Aircraft turbomachine comprising a compartment equipped with a ventilation assembly 有权

    公开(公告)号：US10590799B2

    公开(公告)日：2020-03-17

    申请号：US16162710

    申请日：2018-10-17

    Applicant: Airbus Operations SAS

    Inventor： Maxime Zebian ,  Ali Kapekov

    IPC: F01D25/14 ,  F02C7/18 ,  F01D17/08 ,  F01D25/12

    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.

    Aircraft propulsion assembly having a ventilation system
    4.
    发明授权
    Aircraft propulsion assembly having a ventilation system 有权

    公开(公告)号：US11846233B2

    公开(公告)日：2023-12-19

    申请号：US17181585

    申请日：2021-02-22

    Applicant: Airbus Operations SAS

    Inventor： Yannick Sommerer ,  Maxime Zebian

    IPC: F02C7/18

    CPC classification number: F02C7/18 ,  F05D2260/608

    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.

    Module ensuring an attenuation of sound waves and a heat exchange
    6.
    发明授权
    Module ensuring an attenuation of sound waves and a heat exchange 有权

    公开(公告)号：US12163469B2

    公开(公告)日：2024-12-10

    申请号：US17979023

    申请日：2022-11-02

    Applicant: Airbus Operations SAS

    Inventor： Arnaud Bourhis ,  Florian Ravise ,  Maxime Zebian

    IPC: F02C7/045 ,  F02C7/24 ,  B32B3/12 ,  B64D33/02

    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.

    AIRCRAFT PROPULSION ASSEMBLY HAVING A VENTILATION SYSTEM AND A FIRE-FIGHTING SYSTEM
    9.
    发明申请
    AIRCRAFT PROPULSION ASSEMBLY HAVING A VENTILATION SYSTEM AND A FIRE-FIGHTING SYSTEM 有权

    公开(公告)号：US20220219029A1

    公开(公告)日：2022-07-14

    申请号：US17575389

    申请日：2022-01-13

    Applicant: Airbus Operations SAS

    Inventor： Yannick Sommerer ,  Maxime Zebian

    IPC: A62C3/08 ,  A62C35/02 ,  A62C37/44 ,  F02C7/25

    Abstract: A propulsion assembly with an outer compartment, an inner compartment, a supply pipe and a transfer pipe between the two compartments, a suction system between the two pipes, a regulating element that regulates the flow rate of air in the suction system and a fire-fighting system having a reservoir of extinguishing fluid, a discharge pipe connected to the reservoir, and a control system between the reservoir and the discharge pipe. The discharge pipe is configured and arranged to supply the transfer pipe when the control system is in the open position. The outside air is then driven by the suction system and passes through the two compartments in a forced manner and the extinguishing fluid reaches the transfer pipe to flow into the inner compartment.

    Aircraft turbomachine equipped with a thermoacoustic system
    10.
    发明授权
    Aircraft turbomachine equipped with a thermoacoustic system 有权

    公开(公告)号：US11293349B2

    公开(公告)日：2022-04-05

    申请号：US17158982

    申请日：2021-01-26

    Applicant: Airbus Operations SAS

    Inventor： Thomas Livebardon ,  Maxime Zebian

    IPC: F02C7/24 ,  F02C7/14

    Abstract: A turbomachine for an aircraft, comprising a thermoacoustic system associated with a fluid circuit that serves to supply the engine 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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