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1. 发明授权

US08622341B2 Suspension rudder bar for an aircraft turbojet and a suspension with fan hanger provided therewith 有权
标题翻译：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。

2. 发明申请

US20120011826A1 TURBOJET ENGINE WITH AN ELEMENT OF THE NACELLE ATTACHED TO THE INTERMEDIATE CASING 有权
标题翻译：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
申请人： Emily Barnes , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Yoann Marechal
发明人： Emily Barnes , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Yoann Marechal
IPC分类号： F02K3/06 , F02K1/54
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）。

3. 发明授权

US08919135B2 Turbojet engine with an element of the nacelle attached to the intermediate casing 有权
标题翻译：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
申请人： Emily Barnes , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Yoann Marechal
发明人： Emily Barnes , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Yoann Marechal
IPC分类号： F02C7/20 , F02K3/06
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。

4. 发明申请

US20110259997A1 SUSPENSION RUDDER BAR FOR AN AIRCRAFT TURBOJET AND A SUSPENSION WITH FAN HANGER PROVIDED THEREWITH 有权
标题翻译：用于飞机涡轮机的悬挂式雷管和提供风扇的悬架
公开(公告)号：US20110259997A1
公开(公告)日：2011-10-27
申请号：US13087693
申请日：2011-04-15
申请人： Yoann MARECHAL
发明人： Yoann MARECHAL
IPC分类号： B64D27/10
CPC分类号： B64D27/26
摘要： This invention aims at making a rudder bar with a reduced master-couple in the case of a breaking of a connecting rod. To this end, this invention provides shifting the contact areas to the interior of the rudder bar and thereby reducing the transversal bulk thereof.A suspension rudder bar (140) according to this invention has the shape of a bar (14) with a transversal axis (Y′Y)—symmetrical with respect to a plane (PS) intersecting the rotation axis (X′X) of the engine—and comprises links with transmission connecting rods (130a, 130b) between a rear casing (15) for ejecting gases and a front casing (11) hub (11a) of the fan, and central link means (152, 252) to a fastening fixation (150, 250) to an engine fastening pylon. The links (132a, 132b) of the rudder bar (140) to the transmission connecting rods (130a, 130b) are arranged on the transversal ends (14a, 14b) of the rudder bar (140), and the rudder bar (140, 240) extends, perpendicularly to the axis of the bar (Y′Y), with spars (141a, 141b) over a sufficient portion and at a determined distance from the edges (151c) of the plate (150) for being able to act as an abutment to the plate, with a suitable play, in the case of a torsion around the central link (152) or of a connecting rod (130a, 130b) breaking.
摘要翻译：本发明的目的是在连接杆断裂的情况下制造具有减小的母线的舵杆。为此，本发明提供了将接触区域移动到舵杆内部，从而减小其横向体积。根据本发明的悬架舵杆（140）具有杆（14）的形状，其横向轴线（Y'Y）相对于与旋转轴线（X'X）相交的平面（PS）对称发动机，并且包括与用于喷射气体的后壳体（15）和风扇的前壳体（11）毂（11a）之间的传动连接杆（130a，130b）的连杆，以及中心连杆装置（152,252）紧固固定（150,250）到发动机紧固塔。舵杆（140）与变速器连杆（130a，130b）的连杆（132a，132b）布置在舵杆（140）的横向端（14a，14b）上，舵杆 240）与杆（Y'Y）的轴线垂直地延伸，其中翼梁（141a，141b）在足够的部分上并且距离板（150）的边缘（151c）确定的距离，以便能够作用在围绕中心连杆（152）或连接杆（130a，130b）的扭转的情况下，作为板的邻接件具有合适的游隙。

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