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公开(公告)号：US08523515B2
公开(公告)日：2013-09-03
申请号：US12946259
申请日：2010-11-15
CPC分类号： F03D1/0683 , F03D1/0675 , F05B2240/301 , F05B2260/96 , Y02E10/721
摘要： A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further includes a noise reducer configured on a surface of the rotor blade, the noise reducer comprising a plurality of serrations, each of the plurality of serrations defining a centerline. The centerline of each of the plurality of serrations defines a individual tailored angle dependent on at least one of span-wise location, local chord, width, length, bend angle, and thickness.
摘要翻译： 公开了一种用于风力涡轮机的转子叶片组件。 转子叶片组件包括具有限定压力侧，吸力侧，前缘和在尖端和根部之间延伸的后缘的表面的转子叶片。 转子叶片还包括构造在转子叶片的表面上的减噪器，所述降噪器包括多个锯齿，所述多个锯齿中的每一个限定中心线。 多个锯齿中的每一个的中心线根据跨度位置，局部弦，宽度，长度，弯曲角度和厚度中的至少一个来定义单独的裁切角度。
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公开(公告)号：US07758296B2
公开(公告)日：2010-07-20
申请号：US10581860
申请日：2004-09-30
申请人： Ingo Borchers , Roger Drobietz , Thomas Lange
发明人： Ingo Borchers , Roger Drobietz , Thomas Lange
IPC分类号： F02C7/045
CPC分类号： F04D29/667 , F01D5/148 , F04D29/563 , F04D29/681 , F04D29/682 , F04D29/684 , Y02T50/673 , Y10S416/50
摘要： In a method for reducing noise generated in a turbo engine with cascades, and a stator-rotor arrangement, in which hydrodynamic pressure fluctuations occurring on the cascades are reduced by varying the surface circulation of at least one section of at least one stator. A structure is provided on one or more stators, influencing the surface circulation of at least one section of the stator.
摘要翻译： 在用于降低在具有级联的涡轮发动机中产生的噪声的方法中，以及通过改变至少一个定子的至少一个部分的表面循环来减小在级联中发生的流体动力压力波动的定子 - 转子装置。 一个结构设置在一个或多个定子上，影响定子的至少一个部分的表面循环。
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3.发明申请Aerodynamic Flap Of An Aircraft Having A Device Which Influences The Flap Vortex 失效具有影响襟翼涡流的装置的飞机的气动翼片公开(公告)号：US20090084905A1
公开(公告)日：2009-04-02
申请号：US12280121
申请日：2007-02-23
CPC分类号： B64C9/20 , B64C23/06 , B64C23/069 , Y02T50/162 , Y02T50/164
摘要： A high-lift flap of an aircraft is provided having a device for influencing the flap vortex as well as a device for influencing the flap vortex at the lateral edge of the aerodynamic high-lift flap, which can be achieved effectively and at low cost.
摘要翻译： 提供了一种具有用于影响翼片涡流的装置的飞行器的高升降翼，以及用于影响空气动力学高升降挡板的侧边缘处的翼片涡流的装置，其可以有效且低成本地实现。
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公开(公告)号：US08430638B2
公开(公告)日：2013-04-30
申请号：US13329426
申请日：2011-12-19
IPC分类号： F03D11/00
CPC分类号： F03D1/0633 , F03D1/0675 , F05B2260/96 , F05B2280/4003 , F05B2280/5001 , F05B2280/6013 , Y02E10/721
摘要： A noise reducer for a rotor blade of a wind turbine and a rotor blade assembly are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root. The rotor blade further defines a span and a chord. The rotor blade assembly further includes a noise reducer configured on the rotor blade. The noise reducer includes a plurality of rods each having a body extending between a first end and a second end. The body of each of the plurality of rods contacts and extends parallel to the body of a neighboring rod of the plurality of rods when the noise reducer is in a stable position.
摘要翻译： 公开了一种用于风力涡轮机的转子叶片和转子叶片组件的减噪器。 转子叶片组件包括具有限定压力侧，吸力侧，前缘和后缘的外表面的转子叶片，其各自在尖端和根部之间延伸。 转子叶片进一步限定跨度和弦。 转子叶片组件还包括构造在转子叶片上的减噪器。 减噪器包括多个杆，每个杆具有在第一端和第二端之间延伸的主体。 当减噪器处于稳定位置时，多个杆中的每一个的主体接触并平行于多个杆的相邻杆的主体延伸。
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5.发明授权Aerodynamic flap of an aircraft having a device which influences the flap vortex 失效具有影响翼片涡流的装置的飞行器的气动翼片公开(公告)号：US08096513B2
公开(公告)日：2012-01-17
申请号：US12280121
申请日：2007-02-23
IPC分类号： B64C23/06
CPC分类号： B64C9/20 , B64C23/06 , B64C23/069 , Y02T50/162 , Y02T50/164
摘要： A high-lift flap of an aircraft is provided having a device for influencing the flap vortex as well as a device for influencing the flap vortex at the lateral edge of the aerodynamic high-lift flap, which can be achieved effectively and at low cost.
摘要翻译： 提供了一种具有用于影响翼片涡流的装置的飞行器的高升降翼，以及用于影响空气动力学高升降翼的侧边缘处的翼片涡流的装置，其可以有效且低成本地实现。
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公开(公告)号：US20070274823A1
公开(公告)日：2007-11-29
申请号：US10581860
申请日：2004-09-30
申请人： Ingo Borchers , Roger Drobietz , Thomas Lange
发明人： Ingo Borchers , Roger Drobietz , Thomas Lange
IPC分类号： F02C7/045
CPC分类号： F04D29/667 , F01D5/148 , F04D29/563 , F04D29/681 , F04D29/682 , F04D29/684 , Y02T50/673 , Y10S416/50
摘要： In a method for reducing noise generated in a turbo engine with cascades, and a stator-rotor arrangement, in which hydrodynamic pressure fluctuations occurring on the cascades are reduced by varying the surface circulation of at least one section of at least one stator. A structure is provided on one or more stators, influencing the surface circulation of at least one section of the stator.
摘要翻译： 在用于降低在具有级联的涡轮发动机中产生的噪声的方法中，以及通过改变至少一个定子的至少一个部分的表面循环来减小在级联中发生的流体动力压力波动的定子 - 转子装置。 一个结构设置在一个或多个定子上，影响定子的至少一个部分的表面循环。
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公开(公告)号：US08267657B2
公开(公告)日：2012-09-18
申请号：US12970119
申请日：2010-12-16
IPC分类号： F04D29/38
CPC分类号： F03D1/0675 , F03D80/00 , F05B2250/183 , F05B2260/96 , Y02E10/721
摘要： A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes a noise reducer configured on a surface of the rotor blade. The noise reducer includes a plurality of noise reduction features and a plurality of auxiliary noise reduction features. Each of the plurality of auxiliary noise reduction features is configured on one of the plurality of noise reduction features.
摘要翻译： 公开了一种用于风力涡轮机的转子叶片组件。 转子叶片组件包括具有限定压力侧，吸力侧，前缘和在尖端和根部之间延伸的后缘的表面的转子叶片。 转子叶片组件还包括构造在转子叶片的表面上的减噪器。 降噪器包括多个降噪特征和多个辅助降噪特征。 多个辅助降噪特征中的每一个被配置在多个降噪特征中的一个上。
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公开(公告)号：US20110142666A1
公开(公告)日：2011-06-16
申请号：US12946259
申请日：2010-11-15
IPC分类号： F03D11/00
CPC分类号： F03D1/0683 , F03D1/0675 , F05B2240/301 , F05B2260/96 , Y02E10/721
摘要： A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further includes a noise reducer configured on a surface of the rotor blade, the noise reducer comprising a plurality of serrations, each of the plurality of serrations defining a centerline. The centerline of each of the plurality of serrations defines a individual tailored angle dependent on at least one of span-wise location, local chord, width, length, bend angle, and thickness
摘要翻译： 公开了一种用于风力涡轮机的转子叶片组件。 转子叶片组件包括具有限定压力侧，吸力侧，前缘和在尖端和根部之间延伸的后缘的表面的转子叶片。 转子叶片还包括构造在转子叶片的表面上的减噪器，所述降噪器包括多个锯齿，所述多个锯齿中的每一个限定中心线。 多个锯齿中的每一个的中心线限定取决于跨度位置，局部弦，宽度，长度，弯曲角度和厚度中的至少一个的单独定制的角度
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公开(公告)号：US20080308345A1
公开(公告)日：2008-12-18
申请号：US10592932
申请日：2005-01-20
申请人： Ingo Udo Borchers , Roger Drobietz , Roland Uhlig
发明人： Ingo Udo Borchers , Roger Drobietz , Roland Uhlig
IPC分类号： F01N1/24
CPC分类号： G10K11/172 , F01D25/30 , F02C7/24 , F02K1/827 , F23R2900/00014
摘要： An assembly is provided for reducing the noise that is generated in the heating gas zone by turbofan engines. The assembly consists of an acoustically absorbent cladding in the heating gas flow channel of the turbofan engine. The cladding includes a plurality of neighboring cavities, into each of which four horns extends. The mouths of the horns are fixed to a perforated cover sheet. The cover sheet forms one wall of the heating gas flow channel.
摘要翻译： 提供了一种组件，用于减少涡轮风扇发动机在加热气体区域产生的噪音。 该组件由涡扇发动机的加热气体流动通道中的吸声包层组成。 包层包括多个相邻的空腔，其中四个喇叭延伸。 角的嘴被固定到穿孔的覆盖片上。 覆盖片形成加热气体流动通道的一个壁。
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公开(公告)号：US06491260B2
公开(公告)日：2002-12-10
申请号：US09841699
申请日：2001-04-24
IPC分类号： B64C2306
CPC分类号： B64C21/10 , B64C7/00 , B64C23/06 , Y02T50/162 , Y02T50/166
摘要： Vortex generators are arranged on the edges of aircraft wing control surfaces to generate smaller vortices that weaken the main vortex that would otherwise be generated at these areas, and thereby reduce the aerodynamic generation of noise. Each vortex generator includes plural elongated elements in the form of rigid rods or flexible bristles protruding laterally outwardly from the respective edge of the control surface. The vortex generators are preferably arranged on the inboard and outboard edges of high lift flaps and slats.
摘要翻译： 涡街发生器布置在飞行器机翼控制表面的边缘，以产生更小的涡流，从而削弱否则将在这些区域产生的主涡流，从而减少空气动力学产生的噪音。 每个涡流发生器包括从控制表面的相应边缘横向向外突出的呈刚性杆或柔性刷毛形式的多个细长元件。 涡流发生器优选地布置在高提升襟翼和板条的内侧和外侧边缘上。
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