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    METHOD OF MANUFACTURING A SOUND ABSORBING PANEL
    22.
    发明申请
    METHOD OF MANUFACTURING A SOUND ABSORBING PANEL 有权
    制造吸音板的方法

    公开(公告)号：US20140216846A1

    公开(公告)日：2014-08-07

    申请号：US14245836

    申请日：2014-04-04

    Applicant: AIRCELLE

    Inventor： Herve Hurlin ,  Pierre Caruel

    IPC: G10K11/20 ,  B64D29/00 ,  B64D15/00

    CPC classification number: G10K11/20 ,  B64D15/00 ,  B64D15/04 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  Y10T156/10 ,  Y10T156/1003

    Abstract: The present disclosure provides a method of manufacturing a sound absorbing panel in which a reflective wall on one of faces of a set of sound absorbing cells. In particular, a passage on a portion of a thickness (E) of the set of sound absorbing cells is formed on an opposite face of the one of the faces, while the passage forming a main channel for a communication between sound absorbing cells and for a circulation of a de-icing fluid.

    Abstract translation: 本公开提供一种制造吸声板的方法，其中在一组吸声单元的一个面的一个面上具有反射壁。 特别地，在一个吸音单元的相对面上形成有一组吸声单元的厚度（E）的一部分上的通道，同时通道形成用于吸声单元之间的连通的主通道，并且用于 除冰液的循环。

    De-icing and conditioning device for an aircraft
    24.
    发明授权
    De-icing and conditioning device for an aircraft 有权

    公开(公告)号：US10125683B2

    公开(公告)日：2018-11-13

    申请号：US14974427

    申请日：2015-12-18

    Applicant: AIRCELLE

    Inventor： Pierre Caruel ,  Hervé Hurlin

    IPC: F02C7/047 ,  B64D15/04 ,  B64D33/02

    Abstract: The present disclosure provides a device for de-icing an air inlet lip of an aircraft nacelle. The device includes a pre-exchanger, an intake orifice of taking in low-pressure air downstream from a fan, and two high-pressure air intake orifices downstream from a compressor in addition to controlled valves and check valves installed in an air flow network. In particular, the pre-exchanger includes a low-pressure air outlet capable of opening into the air inlet lip of the aircraft nacelle via a pipe of the air flow network.

    Propulsion unit for an aircraft
    26.
    发明授权
    Propulsion unit for an aircraft 有权

    公开(公告)号：US09957056B2

    公开(公告)日：2018-05-01

    申请号：US14716969

    申请日：2015-05-20

    Applicant: AIRCELLE ,  SNECMA

    Inventor： Patrick Boileau ,  Pierre Caruel ,  Carmen Ancuta ,  Bruno Beutin

    IPC: B64D27/16 ,  B64D29/08 ,  F02K1/78 ,  F02K3/06 ,  B64D29/00

    CPC classification number: B64D27/16 ,  B64D29/00 ,  B64D29/08 ,  F02K1/78 ,  F02K3/06 ,  F05D2230/72

    Abstract: The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.

    COOLING DEVICE FOR A TURBOJET ENGINE OF AN AIRCRAFT NACELLE
    27.
    发明申请
    COOLING DEVICE FOR A TURBOJET ENGINE OF AN AIRCRAFT NACELLE 审中-公开
    用于飞机起重机的涡轮发动机的冷却装置

    公开(公告)号：US20160017751A1

    公开(公告)日：2016-01-21

    申请号：US14865072

    申请日：2015-09-25

    Applicant: AIRCELLE

    Inventor： Pierre Caruel

    IPC: F01D25/12 ,  F01D25/02 ,  F01D25/24

    CPC classification number: F01D25/12 ,  F01D25/02 ,  F01D25/24 ,  F02C7/047 ,  F02C7/14 ,  F05D2220/10 ,  F05D2260/213 ,  Y02T50/675

    Abstract: The present disclosure provides a cooling device for a turbo engine of an aircraft nacelle, including: a heat exchanger and an air outlet pipe. The nacelle includes a front housing that has a front lip forming a hollow leading edge that delimits an annular de-icing chamber. In particular, the cooling device further includes a pipe for supplying pressurized air that extends from an inlet end linked to a pressurized air source, to an outlet end forming an air ejection nozzle opening into the de-icing chamber, and the outlet pipe of the heat exchanger has an air outlet section that is arranged in the de-icing chamber in a position designed such that the pressurized air ejection nozzle forms an air suction pump in the outlet pipe of the exchanger.

    Abstract translation: 本公开提供了一种用于飞机机舱的涡轮发动机的冷却装置，包括：热交换器和出气管。 机舱包括前壳体，其具有形成限定环形除冰室的中空前缘的前唇缘。 特别地，冷却装置还包括用于供应从连接到加压空气源的入口端延伸的加压空气到形成到除冰室中的空气喷射喷嘴开口的出口端的管，以及 热交换器具有排气部，该排气部布置在除冰室内，该设计使得加压空气喷射喷嘴在换热器的出口管中形成空气抽吸泵。

    AIRCRAFT PROPULSION UNIT INCLUDING AT LEAST ONE TURBOJET ENGINE AND A NACELLE
    28.
    发明申请
    AIRCRAFT PROPULSION UNIT INCLUDING AT LEAST ONE TURBOJET ENGINE AND A NACELLE 有权
    飞机推进单元，包括至少一台涡轮发动机和一个NACELLE

    公开(公告)号：US20140137541A1

    公开(公告)日：2014-05-22

    申请号：US14166159

    申请日：2014-01-28

    Applicant: AIRCELLE

    Inventor： Pierre Caruel

    IPC: F02K1/62

    CPC classification number: F02K1/625 ,  F02K1/72 ,  F02K3/06

    Abstract: The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream.

    Abstract translation: 本发明涉及一种用于双流涡轮喷气发动机的机舱，其包括在机舱的周边上具有非恒定横截面的冷气流，使得至少一个挡板相对于所述机舱的中心轴线径向偏移 涡轮喷气发动机相对于相邻的翼片。 用于驱动径向偏移襟翼的系统适于确保襟翼的运动学相对于沿空气流的周边的其余部分安装的襟翼的运动学而偏移。

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