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1.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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2.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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3.发明授权Suspension rudder bar for an aircraft turbojet and a suspension with fan hanger provided therewith 有权用于飞机涡轮喷气发动机的悬架舵杆和具有风扇悬挂器的悬架公开(公告)号：US08622341B2
公开(公告)日：2014-01-07
申请号：US13087693
申请日：2011-04-15
申请人： Yoann Marechal
发明人： Yoann Marechal
IPC分类号： B64D27/00
CPC分类号： B64D27/26
摘要： A suspension rudder bar has the shape of a bar with a transversal axis (Y′Y), symmetrical with respect to a plane (PS) intersecting the rotation axis (X′X) of the engine, and includes links with transmission connecting rods between a rear casing for ejecting gases and a front casing hub of the fan, and a central link to a fastening fixation to an engine fastening pylon. The links of the rudder bar to the transmission connecting rods are arranged on the transversal ends of the rudder bar, and the rudder bar extends, perpendicularly to the axis of the bar (Y′Y), with spars over a sufficient portion and at a determined distance from the edges of the plate to act as an abutment to the plate in the case of a torsion around the central link or of a connecting rod breaking.
摘要翻译： 悬架舵杆具有横向轴线（Y'Y）的形状，其相对于与发动机的旋转轴线（X'X）相交的平面（PS）对称，并且包括与传动连接杆 用于喷射气体的后壳体和风扇的前壳体毂，以及到发动机紧固塔架的紧固固定件的中心连杆。 舵杆与变速器连杆的连杆布置在舵杆的横向端部上，舵杆垂直于杆（Y'Y）的轴线延伸，并具有足够的部分和 在围绕中心连杆或连杆破裂的情况下，从板的边缘确定距离以作为与板的邻接。
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