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    ACOUSTIC PANEL FOR A TURBINE ENGINE
    3.
    发明公开
    ACOUSTIC PANEL FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：US20240191656A1

    公开(公告)日：2024-06-13

    申请号：US18554958

    申请日：2022-04-11

    申请人： SAFRAN NACELLES

    发明人： Marc VERSAEVEL ,  Bertrand Léon Marie DESJOYEAUX ,  Pierre-Yves GINI

    IPC分类号： F02C7/045

    CPC分类号： F02C7/045

    摘要： An acoustic panel for a turbine engine includes a first strip and a second strip each comprising an alternation of first ridges and second ridges connected by sidewalls. The first and second strips are joined to each other to form a plurality of cells, each delimited by a first ridge of the first strip and a first ridge of the second strip. A third strip is interposed between the first strip and the second strip and includes a first lateral wall bearing on the first strip The third strip further includes at least one tab that extends inside one of the cells and delimits all or part of a passage inside the associated cell.

    PROPULSION FLOW PATH DUCT SYSTEMS AND METHODS
    8.
    发明公开
    PROPULSION FLOW PATH DUCT SYSTEMS AND METHODS 审中-公开

    公开(公告)号：US20230407775A1

    公开(公告)日：2023-12-21

    申请号：US18458588

    申请日：2023-08-30

    申请人： THE BOEING COMPANY

    发明人： Michael Hayes ,  Keith A. Etling ,  Jordan Kreitzman ,  Rehan Kaluarachchi ,  Manny Urcia ,  Andrews Guadron

    IPC分类号： F01N1/02 ,  B64D27/00 ,  G10K11/16 ,  G10K11/172 ,  F02C7/045

    CPC分类号： F01N1/023 ,  B64D27/00 ,  G10K11/161 ,  G10K11/172 ,  F02C7/045 ,  F02C6/20

    摘要： A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.

    Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
    9.
    发明授权
    Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air 有权

    公开(公告)号：US11608781B2

    公开(公告)日：2023-03-21

    申请号：US17427563

    申请日：2020-01-22

    申请人： SAFRAN NACELLES

    发明人： Sébastien Laurent Marie Pascal ,  Jean-Michel Paul Ernest Nogues ,  Marc Versaevel ,  François Chauveau

    IPC分类号： F02C7/047 ,  F02C7/045

    摘要： The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall facing the axis X and an outer wall for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.

    Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
    10.
    发明授权
    Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air 有权

    公开(公告)号：US11591960B2

    公开(公告)日：2023-02-28

    申请号：US17427548

    申请日：2020-01-22

    申请人： SAFRAN NACELLES

    发明人： Sébastien Laurent Marie Pascal ,  Jean-Michel Paul Ernest Nogues ,  Marc Versaevel ,  François Chauveau

    IPC分类号： F02C7/045 ,  F02C7/047 ,  B64D15/04

    摘要： The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.