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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：US08500410B2
公开(公告)日：2013-08-06
申请号：US12720226
申请日：2010-03-09
IPC分类号： F01D5/16
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： A blade made of composite material including an airfoil 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; and a device for damping the vibrations incorporated in one or other of the intrados and extrados walls is disclosed. The damping device is formed of at least one layer made of viscoelastic material and a layer made of rigid material, these layers being superposed. The layer made of rigid material includes a first zone and a second zone. The layer made of viscoelastic material is interposed between the airfoil and the first zone of the rigid layer, and the second zone of the rigid layer is attached to the wall of the airfoil without interposition of viscoelastic material.
摘要翻译： 由复合材料制成的刀片，其包括由长丝或纤维形成的机翼，任选地编织，浸渍有可热固化的树脂，在前缘和后缘之间具有内壁和外壁; 并且公开了一种用于阻尼结合在一个或另一个内部和外部壁中的振动的装置。 阻尼装置由至少一层由粘弹性材料制成的层和由刚性材料制成的层形成，这些层被重叠。 由刚性材料制成的层包括第一区和第二区。 由粘弹性材料制成的层插入到翼型件和刚性层的第一区之间，刚性层的第二区域连接到翼型件的壁上而不插入粘弹性材料。
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3.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。
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4.发明授权Lever for rotating a turbomachine variable-pitch stator vane about its pivot 有权用于围绕其枢轴旋转涡轮机械可变节距定子叶片的杠杆公开(公告)号：US08197190B2
公开(公告)日：2012-06-12
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： F01D25/04
CPC分类号： F01D17/165 , F01D17/16 , F04D29/563 , F05D2260/50 , F05D2300/501 , Y10T74/20582
摘要： A lever for rotating about its pivot a turbomachine variable-pitch stator vane: including a first zone for attachment to a lever drive member, a second zone for attachment to the variable-pitch stator vane, and a third zone of elongate shape between the first zone and the second zone is disclosed. A vibration-damping laminate is applied to at least one surface portion of at least one of the zones of the lever. The laminate includes at least one layer of viscoelastic material in contact with the surface portion and a backing layer of rigid material.
摘要翻译： 用于围绕其枢轴旋转涡轮机可变节距定子叶片的杆：包括用于附接到杆驱动构件的第一区域，用于附接到可变桨距定子叶片的第二区域和在第一区域之间的细长形状的第三区域 区域和第二区域被公开。 减震层压板被施加到杆的至少一个区域的至少一个表面部分。 层压体包括与表面部分接触的至少一层粘弹性材料和刚性材料的背衬层。
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公开(公告)号：US08061997B2
公开(公告)日：2011-11-22
申请号：US12209537
申请日：2008-09-12
IPC分类号： F01D5/18
CPC分类号： F01D5/147 , F01D5/16 , F01D5/282 , F01D5/288 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2300/133 , F05D2300/501 , F05D2300/603 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： The present invention relates to a blade made of composite, comprising a vane formed of woven filaments impregnated with a thermosetting resin with a protective element in the region of the leading edge of the vane comprising a part in the form of a rigid strip, said strip being secured to the vane. The blade is characterized in that at least one layer of a viscoelastic material is at least partially interposed between said rigid strip and the vane so as to form, with the protective element, a means of damping the vibrations of the vane.
摘要翻译： 本发明涉及一种由复合材料制成的叶片，其包括由浸渍有热固性树脂的织造细丝形成的叶片，该热敏树脂在叶片的前缘区域中具有保护元件，该叶片包括刚性条形的部分，所述条带 固定在叶片上。 叶片的特征在于，至少一层粘弹性材料至少部分地插入在所述刚性带和叶片之间，以便与保护元件形成阻尼叶片的振动的装置。
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公开(公告)号：US20090074586A1
公开(公告)日：2009-03-19
申请号：US12209537
申请日：2008-09-12
IPC分类号： F01D5/16
CPC分类号： F01D5/147 , F01D5/16 , F01D5/282 , F01D5/288 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2300/133 , F05D2300/501 , F05D2300/603 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： The present invention relates to a blade made of composite, comprising a vane formed of woven filaments impregnated with a thermosetting resin with a protective element in the region of the leading edge of the vane comprising a part in the form of a rigid strip, said strip being secured to the vane. The blade is characterized in that at least one layer of a viscoelastic material is at least partially interposed between said rigid strip and the vane so as to form, with the protective element, a means of damping the vibrations of the vane.
摘要翻译： 本发明涉及一种由复合材料制成的叶片，其包括由浸渍有热固性树脂的织造细丝形成的叶片，该热敏树脂在叶片的前缘区域中具有保护元件，该叶片包括刚性条形的部分，所述条带 固定在叶片上。 叶片的特征在于，至少一层粘弹性材料至少部分地插入在所述刚性带和叶片之间，以便与保护元件形成阻尼叶片的振动的装置。
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7.发明授权Diffuser/rectifier assembly for a turbine engine with corrugated downstream walls 有权具有波纹下游壁的涡轮发动机的扩散器/整流器组件公开(公告)号：US09512733B2
公开(公告)日：2016-12-06
申请号：US13148214
申请日：2009-10-21
CPC分类号： F01D9/041 , F02C3/14 , F04D29/44 , F04D29/444 , F05D2250/52 , F23R3/04 , Y02T50/671
摘要： A diffuser-nozzle assembly for mounting at an outlet from a compressor in a turbomachine, the assembly including a nozzle including two substantially cylindrical walls, a radially inner wall and a radially outer wall that are connected together by radial vanes. The walls of the nozzle are extended downstream beyond the radial vanes and the radial spacing therebetween varies downstream from the vanes to be at a minimum substantially in register with the vanes and at a maximum between the vanes.
摘要翻译： 一种扩散器喷嘴组件，其用于安装在涡轮机中的压缩机的出口处，该组件包括喷嘴，该喷嘴包括两个基本上圆柱形的壁，径向内壁和径向外壁，其通过径向叶片连接在一起。 喷嘴的壁延伸到径向叶片的下游，并且它们之间的径向间隔在叶片的下游处变化成与叶片基本上成对准的最小值，并且在叶片之间处于最大值。
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公开(公告)号：US20120018543A1
公开(公告)日：2012-01-26
申请号：US13148214
申请日：2009-10-21
IPC分类号： B05B1/00
CPC分类号： F01D9/041 , F02C3/14 , F04D29/44 , F04D29/444 , F05D2250/52 , F23R3/04 , Y02T50/671
摘要： A diffuser-nozzle assembly for mounting at an outlet from a compressor in a turbomachine, the assembly including a nozzle including two substantially cylindrical walls, a radially inner wall and a radially outer wall that are connected together by radial vanes. The walls of the nozzle are extended downstream beyond the radial vanes and the radial spacing therebetween varies downstream from the vanes to be at a minimum substantially in register with the vanes and at a maximum between the vanes.
摘要翻译： 一种扩散器喷嘴组件，其用于安装在涡轮机中的压缩机的出口处，该组件包括喷嘴，该喷嘴包括两个基本上圆柱形的壁，径向内壁和径向外壁，其通过径向叶片连接在一起。 喷嘴的壁延伸到径向叶片的下游，并且它们之间的径向间隔在叶片的下游处与基本上与叶片对准的最小值处于叶片的最小值处。
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公开(公告)号：US08137073B2
公开(公告)日：2012-03-20
申请号：US11856357
申请日：2007-09-17
申请人： Stephane Rene Julien Giusti , Christophe Jacq , Jean-Pierre Francois Lombard , Arnaud Rene Suffis
发明人： Stephane Rene Julien Giusti , Christophe Jacq , Jean-Pierre Francois Lombard , Arnaud Rene Suffis
IPC分类号： F04D29/38
CPC分类号： F01D5/147 , B29C65/48 , B29C65/483 , B29C65/484 , B29C66/12461 , B29C66/12463 , B29C66/301 , B29C66/53 , B29C66/721 , B29C66/742 , B29L2031/08 , B29L2031/082 , F01D5/282 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2230/23 , F05D2240/303 , F05D2300/133 , F05D2300/501 , F05D2300/506 , F05D2300/702
摘要： The invention relates to a turbomachine blade comprising an aerodynamic surface made of a composite material and extending in a first direction between a leading edge and a trailing edge, and in a second direction between a root and a tip of the blade. The blade includes solid metal reinforcement that is adhesively bonded to the leading edge of its aerodynamic surface, which reinforcement extends along the first direction beyond the leading edge of the aerodynamic surface and along the second direction between the root and the tip, and includes at least one recess for absorbing at least a portion of the energy that results from an impact of a foreign body against the leading edge of the blade.
摘要翻译： 本发明涉及一种涡轮机叶片，其包括由复合材料制成并在前缘和后缘之间沿第一方向延伸的空气动力学表面，并且在叶片的根部和尖端之间沿第二方向延伸。 叶片包括固体粘合到其空气动力学表面的前缘的固体金属加强件，该加强件沿着第一方向延伸超过空气动力学表面的前缘并且沿着根部和尖端之间的第二方向延伸，并且至少包括 一个凹部，用于吸收由异物冲击叶片的前缘引起的能量的至少一部分。
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10.发明申请公开(公告)号：US20100054918A1
公开(公告)日：2010-03-04
申请号：US12548008
申请日：2009-08-26
IPC分类号： F01D5/16
CPC分类号： B64D31/12 , B64C11/48 , F01D5/10 , F01D25/04 , F05D2220/324 , F05D2220/325 , Y02T50/66 , Y02T50/671 , Y02T50/673
摘要： The present invention relates to a method for reducing the vibration levels capable of occurring, in a turbine engine comprising at least one propeller and one coupling structure of the turbine engine, because of the turbulence of aerodynamic origin generated by the coupling structure on the propeller. The method comprises the following steps during the design of the aerodynamic profiles of the propeller and of the coupling structure: an initial configuration of the aerodynamic profiles is defined, the synchronous forced response on the propeller is calculated as a function of the force of harmonic excitation generated by the coupling structure 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 propeller or of the coupling structure, a tangential geometric offset value θ of the individual aerodynamic profiles is determined in order to reduce the term corresponding to the generalized aerodynamic force. The combination of the sections with the tangential offsets therefore defines a new configuration of the aerodynamic profiles that is applied to the aerodynamic profiles of the propeller or of the coupling structure.
摘要翻译： 本发明涉及一种减少在涡轮发动机中能够发生的振动水平的方法，该涡轮发动机包括涡轮发动机的至少一个螺旋桨和一个联接结构，因为由螺旋桨上的联接结构产生的空气动力学起源的紊流。 该方法包括在螺旋桨和耦合结构的空气动力学特性的设计过程中的以下步骤：定义空气动力学特性的初始配置，螺旋桨上的同步强制响应作为谐波激发力的函数计算 由耦合结构产生的，以所述模式的广义气动力的线性函数的形式表示; 对于螺旋桨或耦合结构中的一个的堆叠部分，切向几何偏移值＆amp; 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，切片与切向偏移的组合定义了应用于螺旋桨或耦合结构的空气动力学轮廓的空气动力学轮廓的新配置。
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