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公开(公告)号：US08333344B2
公开(公告)日：2012-12-18
申请号：US12742850
申请日：2008-09-10
IPC分类号： B64D33/02
CPC分类号： F02C7/04 , B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F05D2230/70
摘要： A nacelle includes a central structure intended to surround a fan of a turbojet engine and an air intake structure attached to the central structure and able to channel a flow of air toward the fan. The nacelle includes at least one longitudinal outer panel incorporating an air intake lip. An inner panel includes an acoustic shell ring which downstream end is attached to an upstream end of the central structure and therewith forms a fixed structure of the nacelle. Guide means are entirely attached to the central structure for guiding the outer panel or panels and allowing substantially rectilinear movement of the outer panel towards the upstream end of the nacelle so that the air intake structure can be opened.
摘要翻译： 机舱包括旨在围绕涡轮喷气发动机的风扇的中心结构和附接到中心结构并且能够将空气流引向风扇的进气结构。 机舱包括至少一个并入进气口的纵向外板。 内部面板包括声学壳环，其下游端附接到中心结构的上游端并由此形成机舱的固定结构。 引导装置完全附接到中央结构以引导外板或面板，并且允许外板朝向机舱的上游端基本上直线运动，使得进气结构可以打开。
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2.发明申请AIR INTAKE STRUCTURE TO BE MOUNTED UPSTREAM OF A NACELLE MIDDLE STRUCTURE FOR AIRCRAFT ENGINE, AND NACELLE EQUIPPED WITH SUCH AIR INTAKE STRUCTURE 有权用于飞机发动机的空调中间结构的空气入口结构和装有这种空气吸入结构的空调公开(公告)号：US20100242428A1
公开(公告)日：2010-09-30
申请号：US12681994
申请日：2008-08-28
IPC分类号： F02G3/00
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0233 , F02C7/047 , Y02T50/671
摘要： The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall (7) including a lip (9) and that can be mounted relative to said middle structure so as to move between a rear position and a front position; a wall (11) defining a de-icing compartment (13) in said lip (9); at least one de-icing collector (15) extending in said compartment (13); and at least one hot-air supply duct (17) of said collector (15), that can be rigidly connected to said middle structure. The wall (11) is tightly secured inside said lip (9), and said supply duct (17) is connected to said collector (15) by removable sealing means (27, 29, 31, 35).
摘要翻译： 本发明涉及一种可以安装在用于飞行器发动机的机舱中间结构的上游的进气结构，并且特别地包括：包括唇缘（9）的外壁（7），并且可以相对于所述中间结构 以便在后部位置和前部位置之间移动; 在所述唇缘（9）中限定除冰隔间（13）的壁（11）; 在所述隔室（13）中延伸的至少一个除冰收集器（15）; 以及所述收集器（15）的至少一个热风供应管道（17），其可以刚性地连接到所述中间结构。 壁（11）紧密地固定在所述唇部（9）内，并且所述供应管道（17）通过可移除的密封装置（27,29,31,35）连接到所述收集器（15）。
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公开(公告)号：US20110182727A1
公开(公告)日：2011-07-28
申请号：US13121749
申请日：2009-09-25
IPC分类号： F01D25/24
CPC分类号： B64D29/08 , B64D29/06 , B64D33/02 , B64D2033/0286
摘要： The invention relates to a nacelle (1) for a turbojet engine, comprising: —an air intake structure able to channel a flow of air towards a fan of the turbojet engine and comprising at least one longitudinal outer panel (40) incorporating an air intake lip (4a), —a middle structure (5) intended to surround the said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, —at least one inner panel (41) comprising an acoustic shroud (53), fixed at its downstream end to an upstream end of the middle structure (5) forming therewith a fixed structure of the nacelle (1), and —means (15) of guiding the outer panel or panels (40) which means are able to allow a substantially rectilinear movement of the outer panel (40) in the upstream direction of the nacelle (1) so as to be able to open the air intake structure, the said nacelle (1) comprising reinforcing means (90) designed to react the mechanical loads of the guide means (15) beyond a predetermined deformation thereof as the air intake structure opens.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱（1），包括： - 空气进入结构，其能够将空气流引导到涡轮喷气发动机的风扇，并且包括至少一个纵向外板（40），其包括进气口 唇缘（4a）， - 中间结构（5），其旨在围绕所述风扇并且所述进气结构以其确保空气动力学连续性的方式附接到所述风扇结构， - 至少一个内部面板（41）包括声罩 （53），其下游端固定在所述中间结构（5）的上游端，从而形成所述机舱（1）的固定结构，以及 - 引导所述外板（40）的装置（15） 能够允许外板（40）在机舱（1）的上游方向上基本上直线运动，以便能够打开进气结构，所述机舱（1）包括设计的加强装置（90） 以使引导装置（15）的机械负载超出ap 随着进气结构的打开，其再次变形。
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公开(公告)号：US20100314501A1
公开(公告)日：2010-12-16
申请号：US12811347
申请日：2008-11-28
IPC分类号： F02C7/04
CPC分类号： E05C19/10 , B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , E05B47/0012 , E05B2047/0023 , E05B2047/0086 , F02C7/04 , F05D2230/70
摘要： The invention relates to a nacelle for a turbojet engine that includes an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the middle structure and defining, with the latter, a nacelle fixed structure and, on the other hand, at least one outer longitudinal panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to define a removable air intake structure, characterised in that the removable air intake structure is provided with peripheral locking means including at least one electric lock (10) each capable of interaction with a complementary retaining means (11).
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱，其包括能够引导朝向涡轮喷气发动机的风扇的空气流的进气结构（2），以及用于围绕所述风扇的中间结构，并且将进气结构 为了提供空气动力学连续性，其中，进气结构一方面包括至少一个内板（21），所述至少一个内板（21）附接到所述中间结构并且与所述内板限定了机舱固定结构，另一方面， 至少一个外部纵向板（20）可移除地附接到固定结构并且包括进气口（2a），以便限定可移除进气结构，其特征在于，所述可移除进气结构设置有外围锁定装置， 至少一个电锁（10），每个能够与互补的保持装置（11）相互作用。
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公开(公告)号：US08876041B2
公开(公告)日：2014-11-04
申请号：US12811347
申请日：2008-11-28
CPC分类号： E05C19/10 , B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , E05B47/0012 , E05B2047/0023 , E05B2047/0086 , F02C7/04 , F05D2230/70
摘要： The invention relates to a nacelle for a turbojet engine that includes an air intake structure capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes at least one inner panel attached to the middle structure and defining, with the latter, a nacelle fixed structure and at least one outer longitudinal panel removably attached to the fixed structure and including an air intake lip in order to define a removable air intake structure, wherein the removable air intake structure is provided with a locking device including at least one electric lock capable of interaction with a complementary retention structure.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱，其包括能够引导朝向涡轮喷气发动机的风扇的空气流的进气结构，以及用于围绕所述风扇的中间结构，并且其连接到进气结构，以便 提供空气动力学连续性，其中所述进气结构包括附接到所述中间结构的至少一个内板，并且与所述至少一个内板一起限定机舱固定结构和至少一个可拆卸地附接到所述固定结构的外纵向板，并且包括进气口 为了限定可拆卸的进气结构，其中可移除进气结构设置有锁定装置，该锁定装置包括能够与互补保持结构相互作用的至少一个电锁。
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6.发明申请公开(公告)号：US20110014044A1
公开(公告)日：2011-01-20
申请号：US12865842
申请日：2008-11-21
IPC分类号： F04D29/40
CPC分类号： B64D29/08 , B64D29/06 , B64D2033/0206 , B64D2033/0286 , F02C7/042
摘要： The invention relates to a nacelle for a turbojet engine that comprises an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and an intermediate structure for surrounding said fan and to which the air intake structure is attached in order to ensure aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the intermediate structure and defining with the latter a fixed nacelle structure and, on the other hand, at least one longitudinal outer panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to form a removable air intake structure, characterised in that the air intake structure is provided with peripheral locking means including at least one locking means (10) attached to the inner panel or to the air intake lip and each capable of interacting with an additional retaining means (11) respectively attached to the air intake lip or to the inner panel.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱，其包括能够引导朝向涡轮喷气发动机的风扇的空气流的进气结构（2），以及用于围绕所述风扇的中间结构，并且进气结构被连接到该中空结构 为了确保空气动力学连续性，其中空气进气结构一方面包括至少一个内板（21），其连接到中间结构并且与其后面固定有固定的机舱结构，另一方面至少包括 一个纵向外板（20）可移除地附接到固定结构并且包括进气口（2a），以便形成可移除的进气结构，其特征在于，进气结构设置有外围锁定装置，其包括至少一个锁定 连接到内板或进气口的装置（10），并且每个装置能够与分别连接到进气口的附加保持装置（11）相互作用 或到内板。
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7.发明授权Air intake structure to be mounted upstream of a nacelle middle structure for aircraft engine, and nacelle equipped with such air intake structure 有权用于飞机发动机的机舱中间结构上游的进气结构和配备有这种进气结构的机舱公开(公告)号：US08800258B2
公开(公告)日：2014-08-12
申请号：US12681994
申请日：2008-08-28
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0233 , F02C7/047 , Y02T50/671
摘要： An air intake structure is mounted upstream of a mid-structure of a nacelle for an aircraft engine. The air intake structure includes an external wall incorporating a lip, a partition defining a deicing compartment in the lip, a deicing manifold extending in the compartment, and a duct for supplying hot air to the deicing manifold. In particular, the external wall is mounted movably with respect to the mid-structure between a rear position and a front position, and the duct is connected in a fixed manner to the mid-structure. The partition is fixed in a sealed manner inside the lip, and the duct is connected to the manifold by a disconnectable seal which is situated in an immediate vicinity of the partition.
摘要翻译： 进气结构安装在用于飞行器发动机的机舱的中间结构的上游。 进气结构包括外壁，其包括唇缘，在唇缘中限定除冰室的隔板，在隔室中延伸的除冰歧管以及用于向除冰歧管供应热空气的管道。 特别地，外壁相对于后部位置和前部位置之间的中间结构可移动地安装，并且管道以固定的方式连接到中间结构。 分隔件以密封的方式固定在唇部内部，并且管道通过位于分隔件紧邻处的可断开的密封件连接到歧管。
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公开(公告)号：US20100252689A1
公开(公告)日：2010-10-07
申请号：US12742850
申请日：2008-09-10
CPC分类号： F02C7/04 , B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F05D2230/70
摘要： The present invention relates to a turbojet engine nacelle (1) comprising:—an air intake structure (4) capable of channelling an airflow towards a fan of the turbojet engine and comprising at least one longitudinal external panel (40) incorporating an air intake lip (4a),—a central structure (5) intended to surround the said fan and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity,—at least one internal panel (41) comprising an acoustic shelving fixed at its downstream end to an upstream end of the central structure (5) therewith forming a fixed structure of the nacelle (1), and—guide means (15) for guiding the external panel or panels (40) which are capable of allowing substantially rectilinear movement of the external panel (40) towards the upstream end of the nacelle (1) so as to be able to open up the air intake structure (4), the guide mans (15) being entirely fixed to the central structure (5).
摘要翻译： 技术领域本发明涉及一种涡轮喷气发动机机舱（1），包括： - 空气进入结构（4），其能够将涡流引导到涡轮喷气发动机的风扇，并且包括至少一个纵向外部面板（40），其包括进气口 （4a）， - 中心结构（5），其旨在围绕所述风扇并且所述进气结构（4）以确保空气动力学连续性的方式附接到所述风扇上， - 至少一个内部面板（41）包括 在其下游端固定到中心结构（5）的上游端的声学架，形成机舱（1）的固定结构，以及引导装置（15），用于引导外部面板或面板（40） 允许外部面板（40）基本上直线运动到机舱（1）的上游端，以便能够打开进气结构（4），导杆（15）完全固定到中心 结构（5）。
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公开(公告)号：US20110219783A1
公开(公告)日：2011-09-15
申请号：US13129290
申请日：2009-08-28
IPC分类号： F02C7/20
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），其包括进气口（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：US20110011981A1
公开(公告)日：2011-01-20
申请号：US12918358
申请日：2009-01-28
IPC分类号： F02C7/047
CPC分类号： B64D33/02 , B64D2033/0233 , B64D2033/0286 , F02C7/047
摘要： The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: —an external wall incorporating a lip, —an upstream partition (108) defining, with the external wall, a deicing compartment (103) in the said lip and comprising an orifice, —a hot air supply device (105) intended to supply the deicing compartment (103) with hot air, the said device (105) comprising a hot air supply tube (107) and a peripheral sealing element (109) surrounding the said supply tube (107), the hot air supply tube (107) having an elbowed free end (111), the orifice (113) in the upstream partition being configured to allow the free end (111) to pass along the main axis (115) of the supply tube, and the sealing element (109) comprising a contact plate (121) surrounding the said tube (107) so as to provide sealing at the upstream partition (108). A further subject of the invention is a nacelle for an aircraft engine comprising such an air intake structure.
摘要翻译： 本发明涉及一种能够安装在用于飞行器发动机的机舱的中心结构的上游的进气结构，所述进气结构包括： - 外部壁，其包含唇缘， - 上游分隔件（108） 所述外壁，所述唇部中的除冰隔间（103）包括孔口， - 用于向所述除冰室（103）供应热空气的热空气供应装置（105），所述装置（105）包括热 空气供应管（107）和围绕所述供应管（107）的周边密封元件（109），所述热空气供应管（107）具有弯头自由端（111），所述上游分隔件中的孔口（113） 被配置为允许自由端（111）沿供应管的主轴线（115）通过，密封元件（109）包括围绕所述管（107）的接触板（121），以便在 上游分区（108）。 本发明的另一个主题是包括这种进气结构的飞机发动机的机舱。
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