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公开(公告)号：US08141817B2
公开(公告)日：2012-03-27
申请号：US12275815
申请日：2008-11-21
申请人： Andre Bruno Denis Baillard , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Francois Raymond Conte , Guillaume Lefort
发明人： Andre Bruno Denis Baillard , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Francois Raymond Conte , Guillaume Lefort
IPC分类号： B64D27/00
CPC分类号： B64D27/26
摘要： A turbojet suspended from an aircraft mast is disclosed. The turbojet includes a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms, and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX. The mast includes a structural strut assembly of elongated shape. The strut assembly is attached upstream rigidly to the outer shroud of the intermediate casing by a front attachment including a device for transmitting the axial and lateral forces and downstream by a rear attachment to the exhaust casing.
摘要翻译： 公开了从飞机桅杆悬挂的涡轮喷气发动机。 涡轮喷气发动机包括前风扇，风扇下游的中间壳体，具有外护罩和通过径向臂连接在一起的毂，以及具有外护罩的排气外壳，两个壳体在同一轴线XX上对准。 桅杆包括细长形状的结构支柱组件。 支柱组件通过前部附件刚性地附接到中间壳体的外护罩上，前部附件包括用于传递轴向和侧向力的装置，并且通过后部附件传递到排气外壳。
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公开(公告)号：US20090134271A1
公开(公告)日：2009-05-28
申请号：US12275815
申请日：2008-11-21
申请人： Andre Bruno Denis Baillard , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Francois Raymond Conte , Guillaume Lefort
发明人： Andre Bruno Denis Baillard , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Francois Raymond Conte , Guillaume Lefort
IPC分类号： B64D27/00
CPC分类号： B64D27/26
摘要： The present invention relates to a turbojet suspended from an aircraft mast, the turbojet comprising a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX, the mast comprising a structural strut assembly of elongated shape. In said turbojet said strut assembly is attached upstream rigidly to said outer shroud of the intermediate casing by a front attachment comprising a means for transmitting the axial and lateral forces and downstream by a rear attachment to said exhaust casing.
摘要翻译： 本发明涉及从飞机桅杆悬挂的涡轮喷气发动机，涡轮喷气发动机包括前风扇，风扇下游具有外护罩的中间壳体和通过径向臂连接在一起的轮毂和具有外护罩的排气外壳， 壳体在同一轴线XX上对准，桅杆包括细长形状的结构支柱组件。 在所述涡轮喷气发动机中，所述支柱组件通过前连接件刚性地附接到所述中间壳体的所述外护罩上，所述前附件包括用于传递所述轴向力和侧向力的装置，并且通过后附件向下排排放到所述排气外壳。
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公开(公告)号：US08104708B2
公开(公告)日：2012-01-31
申请号：US12329136
申请日：2008-12-05
IPC分类号： F02C7/20
CPC分类号： B64D27/26 , B64D2027/268
摘要： The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing.
摘要翻译： 技术领域本发明涉及一种用于将涡轮喷气发动机安装在飞机的塔架上的等静压悬架，该涡轮喷气发动机包括前风扇，具有外壳的风扇下游的中间壳体和通过径向臂互连的轮毂，以及排气 壳体，其具有在相同轴线XX上的外壳，悬架包括在中间壳体上的前部附件，后部附件，其具有连接到排气壳体的外部壳体的至少两个后部附接链节，一对推杆固定在 它们的上游端到达中间壳体的毂。 其特征在于，由后附件的两个连杆形成的平面相对于排气套的平面倾斜。
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公开(公告)号：US20130087635A1
公开(公告)日：2013-04-11
申请号：US13704824
申请日：2011-06-15
IPC分类号： B64D29/00
CPC分类号： B64D29/00 , B64D33/02 , B64D2033/0233 , B64D2033/0286
摘要： An air inlet duct and method for producing such for a turbojet nacelle, the air inlet duct including an upstream annular lip and a downstream outer annular structure. The upstream annular lip and the downstream outer annular structure are formed as a one-piece part made from composite material and the upstream lip is covered with a metal layer formed by electro-deposition or plastic forming. A turbofan engine can include such an air inlet duct.
摘要翻译： 一种用于涡轮喷气发动机舱的空气入口管道及其制造方法，该进气管道包括一个上游环形唇缘和一个下游的外部环形结构。 上游环形唇缘和下游外环形结构形成为由复合材料制成的整体部件，并且上游唇缘被通过电沉积或塑性成形形成的金属层覆盖。 涡轮风扇发动机可以包括这样的进气管道。
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5.发明申请TURBOJET ENGINE WITH AN ELEMENT OF THE NACELLE ATTACHED TO THE INTERMEDIATE CASING 有权涡轮发动机与连接在中间壳体上的NACELLE的元件公开(公告)号：US20120011826A1
公开(公告)日：2012-01-19
申请号：US13179916
申请日：2011-07-11
CPC分类号： F02C7/20 , F02K3/06 , F05D2230/70 , F05D2240/14 , F05D2250/182 , F05D2250/411 , F05D2260/33 , Y02T50/671
摘要： The present invention relates to a turbojet engine with a fan (2) and a nacelle element (2) forming the secondary duct downstream of the fan, the turbojet engine comprising an intermediate casing (6) with an outer shroud (61) to which said nacelle element (8) is fixed by means of a connecting member, wherein the connecting member comprises a cylindrical element (62) secured to the shroud (61) while at the same time being capable of a rotational movement with respect to the axis of the engine and connected to said nacelle element (8) by a bayonet-type fitting.
摘要翻译： 本发明涉及一种具有风扇（2）的涡轮喷气发动机和在风扇下游形成次级风道的机舱元件（2），涡轮喷气发动机包括具有外护罩（61）的中间壳体（6），所述外护罩 机舱元件（8）通过连接构件固定，其中连接构件包括固定到护罩（61）的圆柱形元件（62），同时能够相对于轴线 发动机并通过卡口式配件连接到所述机舱元件（8）。
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6.发明申请METHOD FOR MOUNTING AN AIRCRAFT ENGINE ON A PYLON, AND ENGINE FASTENER FOR IMPLEMENTING SAID METHOD 有权安装PYLON飞机发动机的方法和实施方法的发动机紧固件公开(公告)号：US20140033729A1
公开(公告)日：2014-02-06
申请号：US14110864
申请日：2012-03-30
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , B64D27/26 , B64D2027/266
摘要： A method for mounting an aircraft engine on a pylon includes positioning at least a first shear pin either in a first opening provided in a front engine fastener which is previously attached to the engine using connecting rods, or in a first bore provided in a front surface of the pylon; prepositioning the assembly including the engine and the front engine fastener relative to the pylon by placing the first shear pin opposite a receiving cavity, the receiving cavity being either the first bore, if the first shear pin has been positioned in the first opening, or the first opening, if the first shear pin has been positioned in the first bore; and inserting the first shear pin into the receiving cavity.
摘要翻译： 一种用于将飞机发动机安装在挂架上的方法包括至少将第一剪切销定位在设置在前发动机紧固件中的第一开口中，所述第一开口预先使用连接杆附接到发动机，或者在设置在前表面中的第一孔中 的塔 或者将第一剪切销定位在第一开口中，或者将第一剪切销定位在第一开口中时，接收腔是第一孔，或者， 如果第一剪切销已经定位在第一孔中，则首先打开; 并将第一剪切销插入接收腔。
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公开(公告)号：US09522739B2
公开(公告)日：2016-12-20
申请号：US14128799
申请日：2012-06-13
CPC分类号： B64D27/26 , B64D27/14 , B64D2027/005 , B64D2027/026 , B64D2027/262 , B64D2027/264 , Y02T50/44 , Y02T50/66
摘要： An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective front and rear spars penetrating into the fuselage and fastened to a carrier structure of the aircraft, and including a central longitudinal beam secured at its front end to a first frame, arranged in the plane of the front spar, that is secured at its rear end to a second rear frame, cantilevered out and arranged upstream from the unducted propellers, and that is secured to a third intermediate frame, arranged in the plane of the rear spar between the first and second frames. The first, second, and third frames are connected together by force-takeup beams, an assembly as constituted in this way forming a cradle for receiving the power plant via a standard attachment.
摘要翻译： 一种用于将包括未被引导的螺旋桨的动力装置附接到飞行器的机身上的附接结构，所述附接结构通过第一和第二紧固件连接到相应的前后翼片，所述前后翼片穿透到所述机身中并固定到所述飞行器的承载结构，并且包括 中央纵向梁在其前端固定到第一框架，该第一框架布置在前翼梁的平面中，该第一框架在其后端固定到第二后框架，该第二框架悬臂并布置在未被牵引的推进器的上游，并且被固定 到第三中间框架，布置在第一和第二框架之间的后翼梁的平面中。 第一，第二和第三框架通过受力梁连接在一起，组件以这种方式构成，形成用于经由标准附件接收发电厂的支架。
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8.发明授权公开(公告)号：US09193467B2
公开(公告)日：2015-11-24
申请号：US13243420
申请日：2011-09-23
CPC分类号： B64D27/26 , B64D2027/266
摘要： A suspension for an engine on an aircraft strut is disclosed. The suspension includes a beam with a plate provided with a fixing device for fixing to the strut; and a suspension arch linked to the beam by at least one pivot link whose axis is intended to be parallel to the axis of the engine. The suspension arch having, at each of its ends, a fixing device for fixing to a case of the engine.
摘要翻译： 公开了一种用于飞机支柱上的发动机的悬架。 悬架包括具有设置有固定到支柱的固定装置的板的梁; 以及悬架，其通过至少一个枢轴连接到所述梁，所述至少一个枢轴连接件的轴线旨在平行于所述发动机的轴线。 悬架在其每个端部具有用于固定到发动机壳体的固定装置。
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9.发明授权Turbojet engine with an element of the nacelle attached to the intermediate casing 有权涡轮喷气发动机具有附接到中间壳体的机舱的元件公开(公告)号：US08919135B2
公开(公告)日：2014-12-30
申请号：US13179916
申请日：2011-07-11
CPC分类号： F02C7/20 , F02K3/06 , F05D2230/70 , F05D2240/14 , F05D2250/182 , F05D2250/411 , F05D2260/33 , Y02T50/671
摘要： A turbojet engine with a fan and a nacelle element forming the secondary duct downstream of the fan is provided. The turbojet engine includes an intermediate casing with an outer shroud to which the nacelle element is fixed by a connecting member. The connecting member includes a cylindrical element secured to the shroud while at the same time being capable of a rotational movement with respect to the axis of the engine and connected to the nacelle element by a bayonet-type fitting.
摘要翻译： 提供具有风扇和在风扇下游形成次级风道的机舱元件的涡轮喷气发动机。 涡轮喷气发动机包括具有外护罩的中间壳体，其中机舱元件通过连接构件固定到该壳体上。 连接构件包括固定到护罩的圆柱形元件，同时能够相对于发动机的轴线旋转运动并通过卡口式配件连接到机舱元件。
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10.发明授权公开(公告)号：US09708982B2
公开(公告)日：2017-07-18
申请号：US14110864
申请日：2012-03-30
CPC分类号： F02C7/20 , B64D27/26 , B64D2027/266
摘要： A method for mounting an aircraft engine on a pylon includes positioning at least a first shear pin either in a first opening provided in a front engine fastener which is previously attached to the engine using connecting rods, or in a first bore provided in a front surface of the pylon; prepositioning the assembly including the engine and the front engine fastener relative to the pylon by placing the first shear pin opposite a receiving cavity, the receiving cavity being either the first bore, if the first shear pin has been positioned in the first opening, or the first opening, if the first shear pin has been positioned in the first bore; and inserting the first shear pin into the receiving cavity.
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