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    METHOD FOR REDUCING THE VIBRATION LEVELS OF A PROPFAN OF CONTRAROTATING BLADED DISKS OF A TURBINE ENGINE
    21.
    发明申请
    METHOD FOR REDUCING THE VIBRATION LEVELS OF A PROPFAN OF CONTRAROTATING BLADED DISKS OF A TURBINE ENGINE 有权
    一种减少涡轮发动机叶片混合盘的振动水平的方法

    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。

    LEVER FOR ROTATING A TURBOMACHINE VARIABLE-PITCH STATOR VANE ABOUT ITS PIVOT
    22.
    发明申请
    LEVER FOR ROTATING A TURBOMACHINE VARIABLE-PITCH STATOR VANE ABOUT ITS PIVOT 有权
    用于旋转涡轮增压器的杠杆可变定位器VANE关于其PIVOT

    公开(公告)号：US20090074569A1

    公开(公告)日：2009-03-19

    申请号：US12207009

    申请日：2008-09-09

    申请人： Francois Maurice GARCIN ,  Pierrick Bernard Jean ,  Jean-Pierre Francois Lombard ,  Christian Paleczny

    发明人： Francois Maurice GARCIN ,  Pierrick Bernard Jean ,  Jean-Pierre Francois Lombard ,  Christian Paleczny

    IPC分类号： F04D29/56

    CPC分类号： F01D17/165 ,  F01D17/16 ,  F04D29/563 ,  F05D2260/50 ,  F05D2300/501 ,  Y10T74/20582

    摘要： The present invention relates to a lever for rotating about its pivot a turbomachine variable-pitch stator vane comprising three zones: a first zone for attachment to a lever drive member, a second zone for attachment to said variable-pitch stator vane, and a third zone of elongate shape between the first zone and the second zone, wherein a vibration-damping laminate is applied to at least one surface portion of at least one of said zones of the lever, the laminate comprising at least one layer of viscoelastic material in contact with said surface portion and a backing layer of rigid material.

    摘要翻译： 本发明涉及一种用于围绕其枢轴旋转的杠杆，该涡轮机可变节距定子叶片包括三个区域：用于附接到杆驱动构件的第一区域，用于附接到所述可变节距定子叶片的第二区域，以及第三区域 在所述第一区域和所述第二区域之间的细长形状区域，其中减震层压体被施加到所述杆的至少一个所述区域的至少一个表面部分，所述层压体包括至少一层接触的粘弹性材料层 具有所述表面部分和刚性材料的背衬层。

    Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine
    25.
    发明授权
    Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine 有权
    一种用于降低涡轮发动机反转叶片盘的振动水平的方法

    公开(公告)号：US08375698B2

    公开(公告)日：2013-02-19

    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： F01D25/04 ,  F02K3/072 ,  B21K25/00

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

    摘要： A method for reducing the vibration levels likely to occur, in a turbine engine including 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 is disclosed. The method includes defining an initial configuration of the blades, calculating the synchronous forced response on the first bladed disk as a function of the harmonic excitation force generated by the second bladed disk expressed as a linear function of the generalized aerodynamic force for the mode in question; for stacked sections of one of the two disks, determining a tangential geometric offset value θ of the individual aerodynamic profile to reduce the term corresponding to the generalized aerodynamic force; and applying a new configuration to the blades.

    摘要翻译： 一种用于减少可能发生的振动水平的方法，在涡轮发动机中，由于由气态流体产生的空气动力学原因的湍流，在涡轮发动机中，该涡轮发动机包括形成反转盘的螺旋桨的第一和第二叶片盘， 披露了第一个刀片盘上的第二个刀片盘。 该方法包括定义叶片的初始配置，根据第二叶片盘产生的谐波激励力计算第一叶片盘上的同步强制响应，其表示为所讨论模式的广义气动力的线性函数 ; 对于两个磁盘之一的堆叠部分，确定切向几何偏移值＆amp; 的个体空气动力学特性，以减少对应于广义气动力的术语; 并将新配置应用于刀片。