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公开(公告)号：US20100232974A1
公开(公告)日：2010-09-16
申请号：US12720226
申请日：2010-03-09
CPC分类号： F04D29/324 , F01D5/16 , F04D29/668 , F05D2240/303 , F05D2300/44 , F05D2300/501 , F05D2300/6012 , F05D2300/614 , Y02T50/67 , Y02T50/672 , Y02T50/673
摘要： The present invention relates to a blade made of composite material (100) comprising an airfoil (100A) formed of filaments or fibers, optionally woven, impregnated with a heat-curable resin, with an intrados wall and an extrados wall between the leading edge and the trailing edge.It is characterized in that a device for damping the vibrations is incorporated in one or other of the intrados and extrados walls, and is formed of at least one layer made of viscoelastic material (111) and a layer made of rigid material (110), these layers being superposed. According to one embodiment, the layer made of rigid material comprises a first zone (1101) and a second zone (1102), the layer made of viscoelastic material (111) being interposed between the airfoil and said first zone (1101) of the rigid layer (110), and said second zone (1102) of the rigid layer being attached to the wall of the airfoil (100A) without interposition of viscoelastic material.The invention relates in particular to a turbomachine blade, such as a fan blade of a turbojet engine or a propeller airfoil of a turboprop engine.
摘要翻译： 本发明涉及由复合材料（100）制成的叶片，其包括由长丝或纤维形成的翼片（100A），任选地编织，浸渍有可热固化的树脂，其内部壁和外壁在前缘和 后缘。 其特征在于，用于阻尼振动的装置结合在一个或另一个内部和外部壁中，并且由至少一层由粘弹性材料（111）和由刚性材料（110）制成的层形成， 这些层叠加。 根据一个实施例，由刚性材料制成的层包括第一区域（1101）和第二区域（1102），由粘弹性材料（111）制成的层插入在翼型件和刚性的第一区域（1101）之间 所述刚性层的所述第二区（1102）和所述第二区（1102）附接到所述翼型件（100A）的壁而不插入粘弹性材料。 本发明具体涉及涡轮机叶片，例如涡轮喷气发动机的风扇叶片或涡轮螺旋桨发动机的螺旋桨翼型。
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公开(公告)号：US20060193721A1
公开(公告)日：2006-08-31
申请号：US11359408
申请日：2006-02-23
申请人： Gerard Adam , Xavier Agneray , Kevin Dos Santos , Son Le Hong
发明人： Gerard Adam , Xavier Agneray , Kevin Dos Santos , Son Le Hong
IPC分类号： F04D29/58
CPC分类号： F01D25/246 , F01D25/145 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/231 , F05D2300/614 , Y02T50/675
摘要： The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines. It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.
摘要翻译： 本发明涉及壳体与涡轮机的转子1的动叶片11之间的间隙12的改进，特别是为此目的而设置的壳体，以及装配有这种壳体的涡轮机。 本发明特别适用于飞机涡轮喷气发动机。 更具体地涉及一种涡轮机内壳21，其包括多个环形护罩23，其具有用于将两个相邻的罩23连接在一起的凸缘24。 根据本发明，该内壳21还包括：至少一个圆周热屏蔽5，其覆盖与两个相邻的罩23接触的凸缘24; 以及填充有第一绝热层8的空腔6，所述空腔位于隔热罩5的凹形内表面51a，52a和凸缘24之间。隔热罩5由多个扇形区50形成， 结束
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公开(公告)号：US08225593B2
公开(公告)日：2012-07-24
申请号：US12163504
申请日：2008-06-27
CPC分类号： F02K3/072 , F01D25/16 , F01D25/18 , F05D2220/326 , F05D2220/327 , F05D2260/96
摘要： A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.
摘要翻译： 一种双风扇涡轮机，具有两个反向风扇，一个上游和一个下游，由两个反向同轴轴驱动，每个同轴轴将一个风扇叶轮连接到位于下游的至少一个低压涡轮叶轮，下游风扇叶轮由其下游部分 到其驱动轴。
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公开(公告)号：US20080298972A1
公开(公告)日：2008-12-04
申请号：US12016517
申请日：2008-01-18
申请人： Son Le Hong
发明人： Son Le Hong
IPC分类号： F01D5/02
CPC分类号： F01D5/3007 , F01D21/045 , F04D29/322
摘要： A rotor disk (10) for a fan in a turbomachine, comprising in its perimeter a plurality of essentially axial grooves (22) for the installation and retention of vane roots (20) having hooks at their downstream ends, deformable regions formed by cavities (34) being situated at the downstream end of the grooves (22) in attachment flanges (36) for inter-vane platforms to absorb the stresses between the disk and the vane roots.
摘要翻译： 一种用于涡轮机中的风扇的转子盘（10），其周边包括多个基本上轴向的凹槽（22），用于安装和保持在其下游端具有钩的叶根（20），由空腔形成的可变形区（ 34）位于用于叶片间平台的附接凸缘（36）中的槽（22）的下游端，以吸收盘和叶根之间的应力。
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