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公开(公告)号：US08820344B2
公开(公告)日：2014-09-02
申请号：US13145705
申请日：2010-02-01
CPC分类号： F02C7/04 , B64D29/06 , B64D33/02 , B64D2033/0286 , F05D2240/14 , F05D2250/41 , Y02T50/671 , Y10T137/0536 , Y10T137/0645
摘要： The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside. In addition, the outer structure is equipped with at least one reinforcing beam (10) designed to transmit loads between the annular lip (7) and the cowl (9), said beam (10) extending in the radial plane (P) of the air inlet from the outer structure towards the inner structure and comprising guide means (17) capable of co-operating with complementary guide means (23) belonging to the inner structure. The guide means (17) of the beam (10) and the complementary guide means (23) of the inner structure are offset with respect to the radial plane (P) in which the beam (10) extends.
摘要翻译： 本发明涉及涡轮喷气发动机机舱（1），其包括：外部结构，其包括限定空气入口的环形凸缘和作为所述环形唇缘的延续部延伸的整流罩（9），以及内部固定结构（19），其作为 继续进气口，并包括配备有至少一件需要维护或监控的设备的区域。 上述外部结构可以在整流罩（9）覆盖配备有设备的区域的操作位置与罩（9）显露所述区域的维护位置之间相对于内部结构移动，以便允许进入 设备从外面。 另外，外部结构配备有至少一个加强梁（10），其被设计成在环形唇缘（7）和整流罩（9）之间传递载荷，所述梁（10）在径向平面（P）中延伸 空气入口从外部结构朝向内部结构并且包括能够与属于内部结构的互补引导装置（23）协作的引导装置（17）。 梁（10）的引导装置（17）和内部结构的互补引导装置（23）相对于梁（10）延伸的径向平面（P）偏移。
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公开(公告)号：US20100314198A1
公开(公告)日：2010-12-16
申请号：US12739289
申请日：2008-06-20
摘要： This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.
摘要翻译： 用于飞行器涡轮喷气发动机的机舱的进气口（9）的这种维护手推车（17）是显着的，因为它包括基座（19）和悬臂安装在该基座（19）上的平台（23），并被设计成 进入所述进气口（9）而不与其接触。
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公开(公告)号：US09211956B2
公开(公告)日：2015-12-15
申请号：US13129290
申请日：2009-08-28
CPC分类号： B64D29/08 , B64D2033/0286 , F02C7/04
摘要： Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inner panel of the air intake structure, characterized in that the longitudinal outer panel (40) is associated with guide means of the rails (15)/slide (16) type, at least part of said guide means being positioned as close as possible to an interface with a pylon (2) to which the nacelle is attached.
摘要翻译： 涡轮喷气发动机机舱（1）包括能够将涡流引导到涡轮喷气发动机的风扇的进气结构（4），以及旨在围绕所述风扇并且进气结构附接到其上的中心结构（5） 以确保空气动力学连续性的方式，中心结构一方面包括旨在围绕风扇的壳体，另一方面包括外部结构，其特征在于，进气结构包括纵向外板 （40），其结合有进气口（4a），并且其可以延伸到至少包括所述中心部分的外部结构的至少一部分并且超出所述外部结构，所述纵向外部面板在操作位置之间可平移地移动，在所述操作位置中， 确保机舱外部的空气动力学连续性，以及将外板（40）远离中心部分的外部结构和进气口（4a）设置的维护位置， 远离进气结构的内板，其特征在于，纵向外板（40）与导轨（15）/滑块（16）类型的导向装置相关联，所述导向装置的至少一部分被定位 尽可能靠近与机架相连的塔架（2）的接口。
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公开(公告)号：US09027708B2
公开(公告)日：2015-05-12
申请号：US12739289
申请日：2008-06-20
摘要： This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.
摘要翻译： 用于飞行器涡轮喷气发动机的机舱的进气口（9）的这种维护手推车（17）是显着的，因为它包括基座（19）和悬臂安装在该基座（19）上的平台（23），并被设计成 进入所述进气口（9）而不与其接触。
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公开(公告)号：US08777164B2
公开(公告)日：2014-07-15
申请号：US12918358
申请日：2009-01-28
IPC分类号： B64D15/02
CPC分类号： B64D33/02 , B64D2033/0233 , B64D2033/0286 , F02C7/047
摘要： An air inlet structure which is mounted upstream of a central structure of a nacelle of an aircraft engine includes an outer partition incorporating a lip, an upstream partition defining with the outer partition a deicing compartment in the lip, and a hot air supply device to supply the deicing compartment with hot air. The hot air supply device has a hot air supply tube and a peripheral seal plate surrounding the supply tube. In particular, the hot air supply tube has an elbowed free end, and an orifice of the upstream partition allows passage of the elbowed free end according to a main axis of the supply tube. The seal plate includes a contact plate surrounding the supply tube to ensure sealing at the upstream partition.
摘要翻译： 安装在飞行器发动机的机舱的中心结构的上游的进气口结构包括：外部分隔件，其包括唇缘，上游分隔件与外隔板限定在唇部中的除冰室;以及热空气供应装置， 除冰室内有热风。 热风供给装置具有热供气管和围绕供给管的周边密封板。 特别地，热空气供给管具有弯曲的自由端，并且上游隔板的孔口允许弯曲的自由端根据供应管的主轴线而通过。 密封板包括围绕供应管的接触板，以确保在上游隔板处的密封。
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公开(公告)号：US20110284095A1
公开(公告)日：2011-11-24
申请号：US13145705
申请日：2010-02-01
IPC分类号： F02C7/04
CPC分类号： F02C7/04 , B64D29/06 , B64D33/02 , B64D2033/0286 , F05D2240/14 , F05D2250/41 , Y02T50/671 , Y10T137/0536 , Y10T137/0645
摘要： The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside. In addition, the outer structure is equipped with at least one reinforcing beam (10) designed to transmit loads between the annular lip (7) and the cowl (9), said beam (10) extending in the radial plane (P) of the air inlet from the outer structure towards the inner structure and comprising guide means (17) capable of co-operating with complementary guide means (23) belonging to the inner structure. The guide means (17) of the beam (10) and the complementary guide means (23) of the inner structure are offset with respect to the radial plane (P) in which the beam (10) extends.
摘要翻译： 本发明涉及涡轮喷气发动机机舱（1），其包括：外部结构，其包括限定空气入口的环形凸缘和作为所述环形唇缘的延续部延伸的整流罩（9），以及内部固定结构（19），其作为 继续进气口，并包括配备有至少一件需要维护或监控的设备的区域。 上述外部结构可以在整流罩（9）覆盖配备有设备的区域的操作位置与罩（9）显露所述区域的维护位置之间相对于内部结构移动，以便允许进入 设备从外面。 另外，外部结构配备有至少一个加强梁（10），其被设计成在环形唇缘（7）和整流罩（9）之间传递载荷，所述梁（10）在径向平面（P）中延伸 空气入口从外部结构朝向内部结构并且包括能够与属于内部结构的互补引导装置（23）协作的引导装置（17）。 梁（10）的引导装置（17）和内部结构的互补引导装置（23）相对于梁（10）延伸的径向平面（P）偏移。
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