-
公开(公告)号：US5871176A
公开(公告)日：1999-02-16
申请号：US974559
申请日：1997-11-19
申请人： Fran.cedilla.is Michel Demouzon , Rene Pierre Fer , Patrick Jean Alibert Huet , Laurent Pierre Elysee Gaston Marnas
发明人： Fran.cedilla.is Michel Demouzon , Rene Pierre Fer , Patrick Jean Alibert Huet , Laurent Pierre Elysee Gaston Marnas
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/266 , B64D2027/268
摘要： A redundant front suspension system for a turboshaft engine mounted on a pylon of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device. The primary suspension device comprises a base member secured to the pylon and having a suspension shaft which co-operates with the intermediate casing of the engine, and thrust take-up rods connect the intermediate casing to the base member. The emergency suspension device comprises an additional member which is interposed between the pylon and the base member of the primary device and which has a second shaft at its forward end extending parallel to the longitudinal axis X of the engine, the second shaft being received with clearance in a bore provided in the intermediate casing and being equipped with means for enabling take-up of forces along the X, Y and Z axes in the event of failure of an element of the primary suspension device.
摘要翻译： 安装在飞机的塔架上的用于涡轮轴发动机的冗余前悬架系统包括形成发动机的正常前悬架的主悬架装置和紧急悬挂装置。 主悬挂装置包括固定到塔架上的基座件，并具有与发动机的中间壳体配合的悬挂轴，推力牵引杆将中间壳体连接到基座件上。 紧急悬挂装置包括附加构件，该附加构件介于塔架和主装置的基座构件之间，并且其前端处的第二轴平行于发动机的纵向轴线X延伸，第二轴接收有间隙 在设置在中间壳体中的孔中，并且装备有用于在主悬架装置的元件发生故障的情况下能够沿着X，Y和Z轴的力的吸收的装置。
-
公开(公告)号：US5871177A
公开(公告)日：1999-02-16
申请号：US974678
申请日：1997-11-19
申请人： Francis Michel Demouzon , Rene Pierre Fer , Patrick Jean Alibert Huet , Laurent Pierre Elysee Gaston Marnas
发明人： Francis Michel Demouzon , Rene Pierre Fer , Patrick Jean Alibert Huet , Laurent Pierre Elysee Gaston Marnas
CPC分类号： B64D27/18 , B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A redundant front suspension system for a turboshaft engine mounted on a pylon of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device which operates in the event of failure of the normal suspension. The primary suspension device comprises a base support which is fixed to the pylon and has a suspension shaft which co-operates with the intermediate casing of the engine. Thrust take-up rods connect the intermediate casing to the base support. The emergency suspension device comprises a first support secured to the pylon and a second support secured to the intermediate casing, each of these two supports having a vertical yoke. The vertical yokes are interconnected by a transverse pin which passes through the yokes with a clearance between the pin and one of the yokes. The second support has a vertical pin which is received with clearance in a bore in a horizontal yoke of the first support, the vertical pin and the horizontal yoke taking up the transverse forces in the event of a rupture of the normal suspension shaft. The vertical yokes take up the longitudinal and vertical forces in the event of a rupture of the normal suspension shaft or of a thrust take-up rod.
摘要翻译： 用于安装在飞机的塔架上的涡轮轴发动机的冗余前悬架系统包括形成发动机的正常前悬架的主悬架装置和在正常悬架失效的情况下操作的紧急悬挂装置。 主悬挂装置包括固定在塔架上的基座支架，并具有与发动机的中间壳体配合的悬挂轴。 推力杆将中间套管连接到底座上。 紧急悬挂装置包括固定到塔架的第一支撑件和固定到中间壳体的第二支撑件，这两个支架中的每一个具有垂直轭架。 垂直的轭通过穿过轭的横向销互连，轭与销之间的间隙与轭之间的间隙通过。 第二支撑件具有垂直销，其在第一支撑件的水平轭中的孔中接收间隙，垂直销和水平轭在正常悬挂轴的破裂的情况下承受横向力。 在正常的悬挂轴或推力牵引杆破裂的情况下，垂直的轭体会承受纵向和纵向的力。
-
公开(公告)号：US5871175A
公开(公告)日：1999-02-16
申请号：US974423
申请日：1997-11-19
申请人： Francis Michel Demouzon , Rene Pierre Fer , Patrick Jean Alibert Huet , Laurent Pierre Elysee Gaston Marnas
发明人： Francis Michel Demouzon , Rene Pierre Fer , Patrick Jean Alibert Huet , Laurent Pierre Elysee Gaston Marnas
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/266 , B64D2027/268
摘要： A redundant front suspension system for a turboshaft engine mounted on a on of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device which operates in the event of failure of the normal suspension. The primary suspension device comprises a base support which is fixed to the pylon and has a suspension shaft which co-operates with the intermediate casing of the engine. Thrust take-up rods connect the intermediate casing to the base support. The emergency suspension device comprises a first support secured to the pylon and a second support secured to the intermediate casing, each of these two supports having a vertical yoke associated with it. The vertical yokes are interconnected by a connecting rod in a manner which provides a clearance between the rod and at least one of the yokes. The second support carries a vertical pin which is received with clearance in a bore in a horizontal yoke provided on the first support, the vertical pin and the horizontal yoke taking up the longitudinal and transverse forces in the event of a failure of the normal suspension shaft or of a thrust take-up rod. The connecting rod takes up the vertical forces in the event of a failure of the normal suspension shaft.
摘要翻译： 用于安装在飞机的塔架上的涡轮轴发动机的冗余前悬架系统包括形成发动机的正常前悬架的主悬架装置和在正常悬架失效的情况下操作的紧急悬挂装置。 主悬挂装置包括固定在塔架上的基座支架，并具有与发动机的中间壳体配合的悬挂轴。 推力杆将中间套管连接到底座上。 紧急悬挂装置包括固定到塔架的第一支撑件和固定到中间壳体的第二支撑件，这两个支架中的每一个具有与其相关联的垂直轭。 垂直轭通过连接杆以提供杆和至少一个轭之间的间隙的方式互连。 第二支撑件承载垂直销，其在设置在第一支撑件上的水平轭中的孔中接收间隙，垂直销和水平轭在正常悬挂轴故障的情况下承受纵向和横向力 或推力牵引杆。 在正常悬挂轴故障的情况下，连杆会承受垂直力。
-
公开(公告)号：US20080307795A1
公开(公告)日：2008-12-18
申请号：US12139089
申请日：2008-06-13
申请人： Valentine BADER , Laurent Pierre Elysee Gaston Marnas , Nicolas Pommier , Christian Rene Schnell
发明人： Valentine BADER , Laurent Pierre Elysee Gaston Marnas , Nicolas Pommier , Christian Rene Schnell
CPC分类号： F02C7/00 , F01D25/30 , F02C7/20 , F05D2250/70 , F05D2260/941
摘要： An exhaust casing hub comprises a hub center (6), and an upstream flange (8) and a downstream flange (10) arranged on either side of the hub center. Each flange is terminated by a rim (12). A plurality of cuffs (14) are arranged on the hub center (6) so as to form an angle from the tangent toward the radial direction of 10° to 80°, preferably 15° to 75°. At least one rib is formed at the base of each cuff (14) below a critical stress region (26) in the cuff. The rib is joined to the downstream flange by a downstream end and to the upstream flange by an upstream end.
摘要翻译： 排气套管毂包括轮毂中心（6）和布置在轮毂中心两侧的上游法兰（8）和下游法兰（10）。 每个凸缘由边缘（12）端接。 在轮毂中心（6）上设置有多个袖带（14），从而形成从切线朝向径向的角度为10°〜80°，优选为15°〜75°。 在袖带内的临界应力区域（26）下方的每个箍（14）的基部处形成至少一个肋。 肋通过下游端连接到下游凸缘，并通过上游端连接到上游凸缘。
-
公开(公告)号：US07891165B2
公开(公告)日：2011-02-22
申请号：US12139089
申请日：2008-06-13
申请人： Valentine Bader , Laurent Pierre Elysee Gaston Marnas , Nicolas Pommier , Christian Rene Schnell
发明人： Valentine Bader , Laurent Pierre Elysee Gaston Marnas , Nicolas Pommier , Christian Rene Schnell
IPC分类号： F04D29/02
CPC分类号： F02C7/00 , F01D25/30 , F02C7/20 , F05D2250/70 , F05D2260/941
摘要： An exhaust casing hub includes a hub center, and an upstream flange and a downstream flange arranged on either side of the hub center. Each flange is terminated by a rim. A plurality of cuffs are arranged on the hub center so as to form an angle from the tangent toward the radial direction of 10° to 80° , preferably 15° to 75°. At least one rib is formed at the base of each cuff below a critical stress region in the cuff. The rib is joined to the downstream flange by a downstream end and to the upstream flange by an upstream end.
摘要翻译： 排气套管毂包括轮毂中心，以及布置在轮毂中心两侧的上游法兰和下游法兰。 每个法兰由边缘终止。 在轮毂中心配置有多个袖带，从而形成从切线朝向径向的角度为10°〜80°，优选为15°〜75°。 在袖带的临界应力区域下方的每个袖带的底部形成至少一个肋条。 肋通过下游端连接到下游凸缘，并通过上游端连接到上游凸缘。
-
公开(公告)号：US07849696B2
公开(公告)日：2010-12-14
申请号：US11447109
申请日：2006-06-06
IPC分类号： F02C3/06
摘要： An annular combustion chamber comprising axial walls interconnected by a chamber end wall having a coefficient of thermal expansion that is different from that of the axial walls, the chamber end wall being provided with a plurality of inner and outer fastener tabs secured by fastener systems to the end portions of the axial walls. Each fastener system comprises a bolt, a nut tightened onto one of the ends of the bolt, and a slideway bushing disposed around the bolt between the nut and the end portion of the corresponding axial wall, a determined amount of radial clearance being provided between the nut and the end portion of the axial wall so as to enable the chamber end wall to expand radially freely in operation relative to the axial walls.
摘要翻译： 环形燃烧室包括通过腔室端壁互连的轴向壁，其具有与轴向壁的热膨胀系数不同的热膨胀系数，腔室端壁设置有多个通过紧固件系统固定到内部和外部紧固件接头 轴向壁的端部。 每个紧固件系统包括螺栓，紧固在螺栓的一个端部上的螺母，以及设置在螺母和相应的轴向壁的端部之间的螺栓周围的滑道衬套，确定量的径向间隙设置在 螺母和轴向壁的端部，以便使得腔室端壁能够相对于轴向壁在操作中径向自由地膨胀。
-
7.发明授权公开(公告)号：US07637111B2
公开(公告)日：2009-12-29
申请号：US11410068
申请日：2006-04-25
IPC分类号： F02C3/14
CPC分类号： F23R3/10 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00017
摘要： The component elements of a jet engine combustion chamber are assembled together in a manner that is designed to facilitate maintenance while also improving aerodynamic performance. In an embodiment, the outer cap and the inner cap have tongues and the chamber end wail has corresponding tongues, and the tongues of the caps are assembled to the tongues of the chamber end wall.
摘要翻译： 喷气发动机燃烧室的组成元件以设计成便于维护的方式组装在一起，同时还提高空气动力学性能。 在一个实施例中，外盖和内盖具有舌片，并且腔室端部壁部具有相应的舌片，并且盖子的舌片组装到腔室端壁的舌部。
-
公开(公告)号：US07591136B2
公开(公告)日：2009-09-22
申请号：US11419841
申请日：2006-05-23
IPC分类号： F23R3/28
CPC分类号： F23R3/14 , Y02T50/675
摘要： Injection system of a turbojet engine. It comprises a fixed part and a sliding crossmember. The sliding crossmember comprises a flange capable of sliding on the sliding surface of the fixed part. The fixed part comprises antirotation means and the sliding crossmember of the complementary antirotation means to limit the rotation of the sliding crossmember relative to the fixed part. These means consist of at least one cutout formed in the flange and of at least one lug protruding into said at least one cutout of the flange of the sliding crossmember.
摘要翻译： 涡轮喷气发动机喷油系统 它包括固定部分和滑动横梁。 滑动横梁包括能够在固定部分的滑动表面上滑动的凸缘。 固定部分包括防旋转装置和互补防旋转装置的滑动横梁，以限制滑动横梁相对于固定部分的旋转。 这些装置包括形成在凸缘中的至少一个切口和突出到滑动横梁的凸缘的所述至少一个切口中的至少一个凸耳。
-
-
-
-
-
-
-
搜索结果
8 条记录 (耗时 0.022 秒)
