公开(公告)号：US20070297900A1

公开(公告)日：2007-12-27

申请号：US11763694

申请日：2007-06-15

申请人： Olivier ABGRALL ,  Laurent Gilles DEZOUCHE ,  Francois Maurice GARCIN ,  Jean-Pierre Francois LOMBARD

发明人： Olivier ABGRALL ,  Laurent Gilles DEZOUCHE ,  Francois Maurice GARCIN ,  Jean-Pierre Francois LOMBARD

IPC分类号： F01D9/00 ,  F04D29/54

CPC分类号： F04D29/542 ,  F01D5/225 ,  F01D9/041 ,  F01D11/005 ,  Y02T50/673

摘要： A sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly. It comprises an inner ring sector (4), an outer ring sector (6) and a multitude of blades (8) connecting the inner ring sector (4) to the outer ring sector (6). The outer ring sector (6) or the inner ring sector (4) comprises radial cuts (10) situated between two consecutive blades (8) in such a way as to split them into the same number of elementary sectors as there are blades. Housings (14) are provided, secant to the radial cuts (10), damping inserts (16) being positioned in said housings.

摘要翻译： 压缩机导向叶片组件的扇形部分或涡轮机喷嘴组件的扇形部分。 它包括内环扇区（4），外环扇区（6）和将内环扇区（4）连接到外环扇区（6）的多个叶片（8）。 外圈扇区（6）或内环扇区（4）包括位于两个连续叶片（8）之间的径向切口（10），以便将它们分成与叶片相同数量的基本扇区。 壳体（14）被设置成切割到径向切口（10），阻尼插入件（16）定位在所述壳体中。

公开(公告)号：US20110091310A1

公开(公告)日：2011-04-21

申请号：US12428858

申请日：2009-04-23

申请人： Mathieu CAUCHETEUX ,  Francois Maurice GARCIN ,  Jean-Pierre Francois LOMBARD ,  Nicolas Christian TRICONNET

发明人： Mathieu CAUCHETEUX ,  Francois Maurice GARCIN ,  Jean-Pierre Francois LOMBARD ,  Nicolas Christian TRICONNET

IPC分类号： F04D27/02 ,  F03B11/00

CPC分类号： F01D11/001 ,  F01D11/122 ,  F16J15/445

摘要： The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly.

摘要翻译： 本发明涉及一种围绕纵向轴线形成旋转体的涡轮机械热机械部件，并且包括用于迷宫式密封件的至少一个可磨损环。 以特征方式，可磨损环由在相邻扇形对对之间呈现不同刚度的角扇区组成。 本发明可应用于压缩机，涡轮机或转子和定子组件。

公开(公告)号：US20090004021A1

公开(公告)日：2009-01-01

申请号：US12144994

申请日：2008-06-24

申请人： Stephane Jean Joseph BAUMHAUER ,  Jerome Alain DUPEUX ,  Francois Maurice GARCIN ,  Jean-Pierre Francois LOMBARD ,  Eric SEINTURIER ,  Etienne BALMES

发明人： Stephane Jean Joseph BAUMHAUER ,  Jerome Alain DUPEUX ,  Francois Maurice GARCIN ,  Jean-Pierre Francois LOMBARD ,  Eric SEINTURIER ,  Etienne BALMES

IPC分类号： F01D5/14

CPC分类号： F16F9/306 ,  F01D5/10 ,  F01D25/06 ,  F05D2260/96 ,  Y02T50/673

摘要： The impeller comprises a blade and a support of said blade which extend substantially radially. It also comprises at least one intermediate part extending, in a substantially axial direction, between said blade and said support of the blade, and at least one damping means placed on at least one face of said intermediate part. The damping means is segmented in an axial and/or circumferential direction into at least two elementary damping means.

摘要翻译： 叶轮包括叶片和基本上径向延伸的所述叶片的支撑件。 它还包括至少一个中间部分，其在基本上轴向方向上延伸在所述叶片和叶片的所述支撑件之间，以及至少一个阻尼装置，其设置在所述中间部分的至少一个面上。 阻尼装置在轴向和/或圆周方向上分成至少两个基本阻尼装置。

公开(公告)号：US20100050594A1

公开(公告)日：2010-03-04

申请号：US12548040

申请日：2009-08-26

申请人： Jean-Pierre Francois LOMBARD ,  Jerome Talbotec

发明人： Jean-Pierre Francois LOMBARD ,  Jerome Talbotec

IPC分类号： F02K3/072

CPC分类号： F01D5/16 ,  F01D5/142 ,  F02K3/072 ,  F05D2200/20 ,  F05D2260/80 ,  F05D2260/96 ,  Y10T29/49321

摘要： The present invention relates to a method for reducing the vibration levels likely to occur, in a turbine engine comprising a first and a second bladed disk forming a propfan of contrarotating disks, when the two disks are traversed by a gaseous fluid, because of the turbulence of aerodynamic origin generated by the second bladed disk on the first bladed disk. The method comprises the following steps during the design of said two bladed disks: an initial configuration of the blades is defined, the synchronous forced response is calculated on the first bladed disk as a function of the harmonic excitation force generated by the second bladed disk expressed in the form of a linear function of the generalized aerodynamic force for the mode in question; for stacked sections of one of the two disks, a tangential geometric offset value θ of the individual aerodynamic profile is determined so as to reduce the term corresponding to the generalized aerodynamic force. The combination of the individual profiles on the sections with the tangential offsets therefore defines a new configuration of the blades of said one of the two disks which is applied to the blades of said one of the two disks.

摘要翻译： 本发明涉及一种在涡轮发动机中减少可能发生的振动水平的方法，该涡轮发动机包括第一和第二叶片，其形成反向盘的螺旋，当两个圆盘被气态流体穿过时，由于紊流 由第一个叶片盘上的第二个叶片产生的空气动力学起源。 该方法包括在所述两个叶片盘的设计过程中的以下步骤：限定叶片的初始配置，在第一叶片盘上计算同步强制响应作为由第二叶片盘产生的谐波激发力的函数 以所述模式的广义气动力的线性函数的形式; 对于两个磁盘中的一个的堆叠部分，切线几何偏移值＆Thetas; 确定各个空气动力学特性，以便减少对应于广义气动力的项。 因此，具有切向偏移的部分上的单个轮廓的组合定义了施加到两个盘中的所述一个的刀片之间的两个盘中的所述一个的刀片的新配置。