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1.发明授权Method for reducing the vibration levels of a propeller of a turbine engine 有权一种用于降低涡轮发动机的螺旋桨的振动水平的方法公开(公告)号：US08398372B2
公开(公告)日：2013-03-19
申请号：US12548008
申请日：2009-08-26
CPC分类号： B64D31/12 , B64C11/48 , F01D5/10 , F01D25/04 , F05D2220/324 , F05D2220/325 , Y02T50/66 , Y02T50/671 , Y02T50/673
摘要： A method for reducing the vibration levels capable of occurring, in a turbine engine including 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 includes: defining an initial configuration of the aerodynamic profiles, calculating the synchronous forced response on the propeller 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, and determining a tangential geometric offset value θ of the individual aerodynamic profiles for stacked sections of one of the propeller or of the coupling structure 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.
摘要翻译： 由于由螺旋桨上的联接结构产生的空气动力学起源的湍流，在涡轮发动机中减少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。 该方法包括：定义空气动力学分布的初始配置，计算螺旋桨上的同步强制响应作为由耦合结构产生的谐波激励力的函数，该耦合结构以用于线性函数的广义气动力的线性函数的形式表示 模式，并确定切向几何偏移值＆thetas; 的螺旋桨或耦合结构之一的堆叠部分的单个空气动力学轮廓，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空气动力学特性的新配置。
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2.发明授权公开(公告)号：US08286347B2
公开(公告)日：2012-10-16
申请号：US12035966
申请日：2008-02-22
CPC分类号： F01D5/142 , F01D5/16 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49327
摘要： A method for reducing vibration levels in a turbomachine including at least a first and a second bladed wheel, due to aerodynamic perturbations that are produced by the second bladed wheel or an obstacle on the first bladed wheel is disclosed. The method includes: defining an initial configuration of the blades; calculating the synchronous forced response on the first bladed wheel as a function of the harmonic excitation force produced by the second bladed wheel expressed in the form of a linear function of the generalized aerodynamic force for the mode considered; determining a geometric tangential shift value θ for the stacked cross sections of one of the two wheels to reduce the corresponding term to the generalized aerodynamic force. The set of cross sections with the tangential shifts thus defines a new configuration of the blades of one of the two wheels.
摘要翻译： 公开了一种用于减少包括至少第一和第二叶轮的涡轮机中的振动水平的方法，这是由于由第二叶轮产生的空气动力扰动或第一叶片轮上的障碍物。 该方法包括：定义刀片的初始配置; 根据所考虑的模式的广义气动力的线性函数的形式，计算第一叶片轮上的同步强制响应作为由第二叶片轮产生的谐波激励力的函数; 确定几何切向位移值＆amp; 对于两个车轮之一的堆叠横截面，将相应的术语减小到广义气动力。 因此，具有切向位移的一组横截面限定了两个轮之一的叶片的新构造。
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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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4.发明申请TURBOMACHINE CASING INCLUDING A DEVICE FOR PREVENTING INSTABILITY DURING CONTACT BETWEEN THE CASING AND THE ROTOR 有权涡轮机壳，包括用于防止车壳和转子之间的接触期间的不稳定性的装置公开(公告)号：US20090297331A1
公开(公告)日：2009-12-03
申请号：US12428140
申请日：2009-04-22
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
CPC分类号： F01D11/122 , F01D25/06 , F01D25/24 , F05D2240/11 , F05D2260/96 , F05D2300/501
摘要： The invention relates to a cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel, the casing including a device for preventing instability during contact between the casing and the bladed wheel. In characteristic manner, said device comprises a succession of elements disposed around the circumference of the casing, and presenting between two adjacent elements, different stiffnesses, the number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan.
摘要翻译： 本发明涉及一种用于涡轮机的圆柱形壳体，其适用于接收装有至少一个叶片轮的转子，该壳体包括用于防止壳体与叶片轮之间的接触期间不稳定的装置。 以特征方式，所述装置包括围绕壳体的圆周设置的一系列元件，并且在两个相邻元件之间呈现不同的刚度，具有相同刚度的元件的数量不等于振动的波数的倍数 要被禁止的叶片轮的模式。 本发明可应用于压缩机，涡轮机或风扇。
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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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公开(公告)号：US20090004000A1
公开(公告)日：2009-01-01
申请号：US12144960
申请日：2008-06-24
申请人： Stephane Jean Joseph BAUMHAUER , Jerome Alain Dupeux , Francois Maurice Garcin , Jean-Pierre Francois Lombard
发明人： Stephane Jean Joseph BAUMHAUER , Jerome Alain Dupeux , Francois Maurice Garcin , Jean-Pierre Francois Lombard
IPC分类号： F01D9/04
CPC分类号： F16F9/306 , F01D9/041 , F01D25/04 , F01D25/246 , F05D2260/96 , Y02T50/67 , Y02T50/672 , Y02T50/673
摘要： The present invention relates to a turbomachine stator forming a stator vane ring or upstream guide vane element comprising a plurality of vanes placed radially between a first inner ring and a second outer ring, the two rings being concentric, the second ring having a cylindrical outer surface portion. The stator is characterized in that, on said outer surface portion, at least one vibration-damping laminate is attached, the laminate comprising at least one layer of viscoelastic material in contact with said surface portion and one counterlayer of rigid material.
摘要翻译： 本发明涉及一种形成定子叶片环或上游引导叶片元件的涡轮机定子，其包括放置在第一内圈和第二外圈之间的多个叶片，所述两个环是同心的，所述第二环具有圆柱形外表面 一部分。 定子的特征在于，在所述外表面部分上安装有至少一个减震层压板，所述层压体包括与所述表面部分接触的至少一层粘弹材料和刚性材料的一个反层。
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公开(公告)号：US20080206058A1
公开(公告)日：2008-08-28
申请号：US12035966
申请日：2008-02-22
CPC分类号： F01D5/142 , F01D5/16 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49327
摘要： The present invention concerns a method for reducing vibration levels likely to occur in a turbomachine comprising at least a first and a second bladed wheel, where the two wheels are moving relative to one another about an axis of rotation and a gaseous fluid is passing over them, due to perturbations of an aerodynamic origin that are produced by the second bladed wheel or an obstacle on the first bladed wheel. The method includes the following steps in the design of said two bladed wheels: an initial configuration of the blades is defined; the synchronous forced response on the first bladed wheel is calculated as a function of the harmonic excitation force produced by the second bladed wheel expressed in the form of a linear function of the generalized aerodynamic force for the mode considered; a geometric tangential shift value θ is determined for the stacked cross sections of one of the two wheels so as to reduce the corresponding term to the generalized aerodynamic force. The set of cross sections with the tangential shifts thus defines a new configuration of the blades of said one of the two wheels which is applied to the blades of said one of the two wheels.
摘要翻译： 本发明涉及一种用于减少可能发生在包括至少第一和第二叶轮的涡轮机中的振动水平的方法，其中两个轮相对于彼此围绕旋转轴线移动并且气体流体在它们之上 由于由第二叶轮产生的空气动力学起源或第一叶片轮上的障碍物的扰动。 该方法在所述两个叶片轮的设计中包括以下步骤：定义叶片的初始构型; 计算第一叶轮上的同步强制响应作为由所考虑的模式的广义气动力的线性函数形式表示的第二叶轮产生的谐波激励力的函数; 为两个车轮之一的堆叠横截面确定几何切向偏移值θ，以便将相应的术语减小到广义气动力。 具有切向位移的一组横截面因此限定了施加到两个车轮中的一个的叶片上的两个车轮之一的叶片的新构造。
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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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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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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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