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    Thrust reverser door with spring biased movable external panel
    45.
    发明授权
    Thrust reverser door with spring biased movable external panel 失效
    推力反向门带弹簧偏置可动外部面板

    公开(公告)号：US5987881A

    公开(公告)日：1999-11-23

    申请号：US041767

    申请日：1998-03-13

    Applicant: Patrick Gonidec ,  Pascal Gerard Rouyer ,  Guy Bernard Vauchel

    Inventor： Patrick Gonidec ,  Pascal Gerard Rouyer ,  Guy Bernard Vauchel

    IPC: B64D33/00 ,  F02K1/70

    CPC classification number: F02K1/70 ,  Y02T50/672

    Abstract: A thrust reverser is disclosed for an aircraft jet engine having a cowling with an outer surface and at least one reverse thrust opening, the thrust reverser including a thrust reverser door assembly movable with respect to the cowling between a forward thrust position, in which the reverse thrust opening is uncovered, and a reverse thrust position in which the thrust reverser door uncovers the reverse thrust opening. The thrust reverser door assembly includes an inner structure, an external panel movably connected to the inner structure and one or more resilient devices acting on the inner structure and the external panel to bias the external panel toward the inner structure such that, when the thrust reverser door is in the forward thrust position the external panel is displaced away from the inner structure by contact with the cowling such that an outer surface of the external panel is substantially flush with the outer surface of the cowling.

    Abstract translation: 公开了一种用于具有外表面和至少一个反推力开口的整流罩的飞机喷气发动机的推力反向器，推力反向器包括可在前推力位置之间相对于整流罩移动的推力反向器门组件，其中相反 推力开口未被覆盖，并且反推力位置中，推力反向器门揭开反向推力开口。 推力反向器门组件包括内部结构，可移动地连接到内部结构的外部面板和作用在内部结构上的一个或多个弹性装置和外部面板，以将外部面板偏向内部结构，使得当推力反向器 门处于向前推力位置，外部板通过与整流罩接触而远离内部结构移位，使得外部面板的外表面与整流罩的外表面基本齐平。

    Jet engine nacelle equipped with a system for mechanically inhibiting a thrust reverser
    46.
    发明授权
    Jet engine nacelle equipped with a system for mechanically inhibiting a thrust reverser 有权
    喷气发动机机舱配备有用于机械地抑制推力反向器的系统

    公开(公告)号：US08631640B2

    公开(公告)日：2014-01-21

    申请号：US12672101

    申请日：2008-06-16

    Applicant: Pascal Gerard Rouyer ,  Emmanuel Lesteven

    Inventor： Pascal Gerard Rouyer ,  Emmanuel Lesteven

    IPC: F02K1/70

    CPC classification number: B64D29/06 ,  B64D29/00 ,  F02K1/72 ,  F02K1/766 ,  Y10T137/0645

    Abstract: The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn from the running track of the rail and allows a translational movement of the movable cowl, and an engaged position, in which it forms a stop capable of preventing the movable cowl from sliding in the downstream direction of the nacelle.

    Abstract translation: 本发明涉及一种喷气式发动机机舱，其包括前进气进口部分，旨在围绕喷气式发动机风扇的中段，以及装备有至少一个推力反转系统的后部，其一方面包括用于偏转的装置 喷气发动机的空气流的至少一部分，另一方面，至少一个整流罩（12），其沿着基本上平行于所述机舱的纵向轴线的方向沿着至少一个导轨（15）平移地安装，所述整流罩 可移动整流罩能够从关闭位置交替地切换，其中它将机舱具有空气动力学连续性并且将偏转装置覆盖到打开位置，在该打开位置中，其打开机舱中的通道并且露出所述偏转装置，所述机舱被表征 其特征在于，所述后部装备有至少一个安装成使得其可以在所述导轨的区域中的所述后部的固定结构的缩回位置之间移动的螺柱（18），所述后部位置 所述螺柱从轨道的运行轨道中撤出，并允许可移动整流罩的平移运动和接合位置，其中它形成能够防止可移动整流罩在机舱的下游方向上滑动的止挡件。

    Method for producing sodium chloride crystals
    47.
    发明授权
    Method for producing sodium chloride crystals 失效
    生产氯化钠晶体的方法

    公开(公告)号：US06692720B1

    公开(公告)日：2004-02-17

    申请号：US09763638

    申请日：2001-08-27

    Applicant: Leon Ninane ,  Cédric Humblot ,  Pascal Gerard

    Inventor： Leon Ninane ,  Cédric Humblot ,  Pascal Gerard

    IPC: C01D316

    CPC classification number: C01D3/16 ,  B01D53/68 ,  C01F11/46

    Abstract: Process for the production of sodium chloride crystals from a sodium chloride brine contaminated by potassium chloride and sulphate ions, according to which a calcium compound (32) is added to the brine (48) to crystallize glauberite (35), which is isolated, the resulting aqueous solution (36) is subjected to evaporation to crystallize sodium chloride (40), which is collected, and the aqueous mother liquor (41) from the crystallization of the sodium chloride is subjected to cooling (42) to crystallize glaserite (45).

    Abstract translation: 由氯化钾和硫酸根离子污染的氯化钠盐水生产氯化钠晶体的方法，根据该方法，将钙化合物（32）加入到盐水（48）中以结晶分离的芒硝（35）， 使得到的水溶液（36）蒸发以结晶收集的氯化钠（40），并将来自氯化钠结晶的母液（41）冷却（42）以结晶闪石（45） 。

    Gas flow guide for an aircraft thrust reverser
    48.
    发明授权
    Gas flow guide for an aircraft thrust reverser 失效
    用于飞机推力反向器的气流引导器

    公开(公告)号：US6029439A

    公开(公告)日：2000-02-29

    申请号：US988957

    申请日：1997-12-11

    Applicant: Patrick Gonidec ,  Pascal Gerard Rouyer ,  Guy Bernard Vauchel

    Inventor： Patrick Gonidec ,  Pascal Gerard Rouyer ,  Guy Bernard Vauchel

    IPC: B64D33/00 ,  F02K1/64 ,  F02K1/70

    CPC classification number: F02K1/70

    Abstract: A gas flow guide is disclosed for an aircraft jet engine thrust reverser having a thrust reverser door movably connected to a cowling so as to move between forward and reverse thrust positions, the cowling having a reverse thrust opening bounded by a forward edge having a deflector, an opposite lateral side edges, an inner surface of the cowling forming an outer boundary of a gas flow duct, a forward inner surface of the thrust reverser door tapering toward an outer surface so as to form a cavity opening into the gas flow duct when the thrust reverser door is in the forward thrust position, wherein the gas flow guide has at least one guide vane connected to the cowling so as to be located within the cavity when the thrust reverser door is in the forward thrust position and located rearwardly of the deflector extending from the forward edge so as to guide the gas passing through the reverse thrust opening when the thrust reverser door is in the reverse thrust position.

    Abstract translation: 公开了一种用于飞机喷气发动机推力反向器的气流引导器，其具有可移动地连接到整流罩的推力反向器门，以便在前进和反向推力位置之间移动，整流罩具有由具有偏转器的前边缘限定的反向推力开口， 整流罩的内表面形成气流管道的外边界，推力反向器门的前内表面朝向外表面逐渐变细，以形成通向气流管道的空腔 推力反向器门处于向前推力位置，其中气体导流器具有连接到整流罩的至少一个导向叶片，以便当推力反向器门处于向前推力位置并位于偏转器后面时位于腔体内 从前缘延伸，以便当推力反向器门处于反向推力位置时引导通过反向推力开口的气体。

    Rear section of aircraft nacelle and nacelle equipped with such rear section
    49.
    发明授权
    Rear section of aircraft nacelle and nacelle equipped with such rear section 有权
    飞机机舱和机舱的后部配备有这样的后部

    公开(公告)号：US08943793B2

    公开(公告)日：2015-02-03

    申请号：US12673288

    申请日：2008-06-16

    Applicant: Eric Lecossais ,  Thierry Ledocte ,  Pascal Gerard Rouyer ,  Felix Carimali

    Inventor： Eric Lecossais ,  Thierry Ledocte ,  Pascal Gerard Rouyer ,  Felix Carimali

    IPC: F02K3/02 ,  B64D29/00

    CPC classification number: B64D29/00

    Abstract: The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.

    Abstract translation: 本发明涉及飞机机舱的后部（11），其包括两个半部（13a，13b），其限定：用于容纳涡轮喷气发动机（7）的中央部分（C），冷空气环形通道（31） 设置在所述中心部分（C）周围，以及设置在所述中心部分（C）下方的至少一个六小时空腔（15）。 后部分的特征在于它包括用于在所述环形通道（31）和所述六小时空腔（15）之间流体连通的至少一个管道（29a，29b），用于保持六小时空腔内的温度（15 ）在相对较低的范围内。

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