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    Airfoils including compliant tip
    1.
    发明授权
    Airfoils including compliant tip 有权
    翼型包括合适的尖端

    公开(公告)号：US09085989B2

    公开(公告)日：2015-07-21

    申请号：US13336001

    申请日：2011-12-23

    申请人： Pranav Dhoj Shah ,  Scott Roger Finn ,  Nicholas Joseph Kray ,  Ian Francis Prentice ,  Dong-Jin Shim ,  Bo Wang

    发明人： Pranav Dhoj Shah ,  Scott Roger Finn ,  Nicholas Joseph Kray ,  Ian Francis Prentice ,  Dong-Jin Shim ,  Bo Wang

    IPC分类号： F01D5/20 ,  F01D21/04

    CPC分类号： F01D5/20 ,  F01D21/045 ,  F05D2300/43 ,  F05D2300/431 ,  F05D2300/432 ,  Y02T50/672 ,  Y02T50/673

    摘要： An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact.

    摘要翻译： 翼型件，风扇组件和发动机包括至少一个包括根部，主体部分和顶端部分的翼型件。 主体部分被配置为从根部径向向外延伸，并且尖端部分被构造成从根部部分和主体部分径向向外延伸。 所述翼型件包括在前缘和后缘处连接在一起并在其间延伸的吸力和压力侧。 所述翼型件在尖端部分包括柔性尖端。 柔性尖端沿着顶端部分的至少一部分沿着弦向和跨度方向延伸。 柔性尖端构造成沿着尖端部分提供波传播，使得在异物冲击期间，靠近尖端部分和后缘的临界应变减小。

    AIRFOILS INCLUDING COMPLIANT TIP
    2.
    发明申请
    AIRFOILS INCLUDING COMPLIANT TIP 有权
    航空器包括合规提示

    公开(公告)号：US20130164140A1

    公开(公告)日：2013-06-27

    申请号：US13336001

    申请日：2011-12-23

    申请人： Pranav Dhoj Shah ,  Scott Roger Finn ,  Nicholas Joseph Kray ,  Ian Francis Prentice ,  Dong-Jin Shim ,  Bo Wang

    发明人： Pranav Dhoj Shah ,  Scott Roger Finn ,  Nicholas Joseph Kray ,  Ian Francis Prentice ,  Dong-Jin Shim ,  Bo Wang

    IPC分类号： F01D5/14

    CPC分类号： F01D5/20 ,  F01D21/045 ,  F05D2300/43 ,  F05D2300/431 ,  F05D2300/432 ,  Y02T50/672 ,  Y02T50/673

    摘要： An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact.

    摘要翻译： 翼型件，风扇组件和发动机包括至少一个包括根部，主体部分和顶端部分的翼型件。 主体部分被配置为从根部径向向外延伸，并且尖端部分被构造成从根部部分和主体部分径向向外延伸。 所述翼型件包括在前缘和后缘处连接在一起并在其间延伸的吸力和压力侧。 所述翼型件在尖端部分包括柔性尖端。 柔性尖端沿着顶端部分的至少一部分沿着弦向和跨度方向延伸。 柔性尖端构造成沿着尖端部分提供波传播，使得在异物冲击期间，靠近尖端部分和后缘的临界应变减小。

    Containment case and method of manufacture
    4.
    发明授权
    Containment case and method of manufacture 有权
    收容箱和制造方法

    公开(公告)号：US09248612B2

    公开(公告)日：2016-02-02

    申请号：US13326455

    申请日：2011-12-15

    申请人： Qi Zhu ,  Scott Roger Finn

    发明人： Qi Zhu ,  Scott Roger Finn

    IPC分类号： A47G19/22 ,  B29C70/08 ,  F01D5/28 ,  F01D25/24 ,  B29L31/00

    CPC分类号： B29C70/08 ,  B29K2995/0089 ,  B29L2031/7504 ,  F01D5/28 ,  F01D5/282 ,  F01D25/24 ,  Y02T50/672

    摘要： A containment case comprises a composite core, with an inner and outer surface, at least one puncture resistant layer bonded to the inner surface of the composite core and at least one energy capture layer bonded to the outer surface of the composite core. The puncture resistant layer having a high through-thickness shear strength and high interlaminar toughness at impact. The energy capture layer having a high in-plane tensile strength and low resistance to delamination and fiber-matrix debonding at impact. A method of fabricating a containment case includes the steps of disposing one or more layers of a puncture resistant material on a layup mandrel, disposing one more layers of a structural composite material on an exterior surface of the puncture resistant material, disposing one or more layers of an energy capture material on an exterior surface of the structural material and curing a resin in the plurality of layers.

    摘要翻译： 容纳壳体包括具有内表面和外表面的复合芯，与复合芯的内表面结合的至少一个抗穿刺层和结合到复合芯的外表面的至少一个能量捕获层。 抗穿刺层在冲击时具有高的穿透厚度的剪切强度和高的层间韧性。 能量捕获层具有高的平面内抗拉强度，并且在冲击时具有低的分层和纤维基质脱粘的抗性。 一种制造容纳壳体的方法包括以下步骤：将一层或多层抗穿刺材料设置在铺层心轴上，在抗穿刺材料的外表面上放置一层结构复合材料，将一层或多层 的能量捕获材料在所述结构材料的外表面上并固化所述多个层中的树脂。

    Multi-component hybrid turbine blade
    5.
    发明授权
    Multi-component hybrid turbine blade 有权
    多组分混合涡轮叶片

    公开(公告)号：US06607358B2

    公开(公告)日：2003-08-19

    申请号：US10040238

    申请日：2002-01-08

    申请人： Scott Roger Finn ,  Jan Christopher Schilling ,  Wendy Wen-Ling Lin ,  Mustafa Dindar ,  Robert Paul Tyler

    发明人： Scott Roger Finn ,  Jan Christopher Schilling ,  Wendy Wen-Ling Lin ,  Mustafa Dindar ,  Robert Paul Tyler

    IPC分类号： F01D514

    CPC分类号： B29D99/0025 ,  B23P15/04 ,  B29C70/345 ,  B29C70/865 ,  B29L2031/08 ,  F01D5/147 ,  F01D5/28 ,  F01D5/282 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/431 ,  F05D2300/50 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

    摘要： A multi-component hybrid turbine blade comprises a shank portion and an airfoil portion. The airfoil portion comprises a composite section having a first density. The composite section comprises a recess and an insert section. The insert section has a second mass density, which is less than the first mass density. The insert section is disposed in the recess, and the insert section is bonded to the composite section. The composite section and the insert section together define an airfoil shape. A fabrication method comprising laying up composite material layers to form a portion of the composite section. The portion of the composite section comprises a recess. Disposing the insert section in the recess. Laying up additional composite material layers to achieve a final desired thickness of the composite section while covering the insert section.

    摘要翻译： 多组分混合涡轮机叶片包括柄部分和翼型部分。 翼型部分包括具有第一密度的复合部分。 复合部分包括凹部和插入部分。 插入部分具有小于第一质量密度的第二质量密度。 插入部设置在凹部中，插入部接合到复合部。 复合部分和插入部分共同限定翼型形状。 一种制造方法，包括铺设复合材料层以形成复合部分的一部分。 复合部分的部分包括凹部。 将插入部分放置在凹槽中。 放置另外的复合材料层以在覆盖插入部分的同时实现复合部分的最终期望厚度。

    MULTI-RESIN COMPOSITE ARTICLES AND SYSTEM AND METHOD OF MANUFACTURE
    6.
    发明申请
    MULTI-RESIN COMPOSITE ARTICLES AND SYSTEM AND METHOD OF MANUFACTURE 有权
    多树脂复合材料及其制造方法及制造方法

    公开(公告)号：US20080305340A1

    公开(公告)日：2008-12-11

    申请号：US11759356

    申请日：2007-06-07

    申请人： Xiaomei Fang ,  Wendy Wen-Ling Lin ,  Ming Xie ,  Scott Roger Finn

    发明人： Xiaomei Fang ,  Wendy Wen-Ling Lin ,  Ming Xie ,  Scott Roger Finn

    IPC分类号： B29C70/48 ,  B29C70/06 ,  B32B5/28 ,  F04D29/40

    CPC分类号： F04D29/023 ,  B29C70/443 ,  B29K2063/00 ,  B29K2995/0089 ,  F04D29/526 ,  F05D2300/43 ,  F05D2300/603 ,  F05D2300/6031 ,  Y10T428/31504

    摘要： A method for manufacturing a multi-resin composite article is provided. The method comprises providing at least one fiber preform in a mold; injecting a plurality of resins into the at least one fiber preform at a plurality of locations on the at least one fiber preform; and forming at least one transition region along a mutual contact surface between the resins. Each of the at least one transition regions is defined by a gradual transition in composition from one of the resins to another of the resins. A multi-resin composite article is also provided. The article comprises: at least one fiber preform; a plurality of resins, wherein the at least one fiber preform is infused with the resins; and at least one transition region extending along a mutual contact surface between respective ones of the resins. A system for manufacturing such a multi-resin composite article is also provided.

    摘要翻译： 提供了一种多树脂复合制品的制造方法。 该方法包括在模具中提供至少一个纤维预制件; 在所述至少一个纤维预制件上的多个位置处将多个树脂注入到所述至少一个纤维预制件中; 以及沿树脂之间的相互接触表面形成至少一个过渡区域。 至少一个过渡区域中的每一个由组合物中的一种树脂到另一种树脂的逐渐过渡来限定。 还提供了多树脂复合制品。 该制品包括：至少一个纤维预制件; 多个树脂，其中所述至少一个纤维预制体被所述树脂注入; 以及沿着相应的树脂之间的相互接触表面延伸的至少一个过渡区域。 还提供了一种用于制造这种多树脂复合制品的系统。

    System and method for passive load attenuation in a wind turbine
    7.
    发明授权
    System and method for passive load attenuation in a wind turbine 有权
    风力发电机中被动负载衰减的系统和方法

    公开(公告)号：US07153090B2

    公开(公告)日：2006-12-26

    申请号：US11015259

    申请日：2004-12-17

    申请人： Guy Wayne DeLeonardo ,  Scott Roger Finn ,  Peter Michael Finnigan ,  Donald Joseph Kasperski

    发明人： Guy Wayne DeLeonardo ,  Scott Roger Finn ,  Peter Michael Finnigan ,  Donald Joseph Kasperski

    IPC分类号： F03B15/06

    CPC分类号： F03D1/0675 ,  F05B2240/30 ,  F05B2240/301 ,  Y02E10/721

    摘要： In accordance with certain embodiments, a wind turbine blade includes an outer skin and an internal support structure. The skin has a closed airfoil shape and includes an outer surface, an inner surface, and opposite sides along a length of the blade. The internal support structure is disposed within the closed airfoil shape. The internal support structure includes at least one shear load bearing member disposed across the opposite sides and oriented lengthwise along the length of the blade. The internal support structure further includes a plurality of bending load bearing members disposed along the inner surface in a lengthwise direction along the length of the blade. The internal support structure is configured to position a shear center and a center of aerodynamic pressure loading of the blade at different locations relative to one another.

    摘要翻译： 根据某些实施例，风力涡轮机叶片包括外部皮肤和内部支撑结构。 皮肤具有封闭的翼型形状并且包括外表面，内表面和沿刀片的长度的相对侧。 内部支撑结构设置在封闭的翼型形状内。 内部支撑结构包括横跨相对侧设置并沿着叶片的长度沿纵向定向的至少一个剪切载荷承载构件。 内部支撑结构还包括多个沿刀片的长度方向沿长度方向沿内表面设置的弯曲载荷承载部件。 内部支撑结构构造成将叶片的剪切中心和空气动力学压力的中心相对于彼此定位在不同的位置。