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    Dual cure compositions, methods of curing thereof and articles therefrom
    3.
    发明申请
    Dual cure compositions, methods of curing thereof and articles therefrom 审中-公开
    双重固化组合物，其固化方法和其制品

    公开(公告)号：US20070066698A1

    公开(公告)日：2007-03-22

    申请号：US11235624

    申请日：2005-09-20

    Applicant: Wenliang Yang ,  Wendy Lin ,  Paul Furuta

    Inventor： Wenliang Yang ,  Wendy Lin ,  Paul Furuta

    IPC: C08F2/50

    CPC classification number: C08F2/48 ,  B32B5/18 ,  B32B5/26 ,  B32B5/28 ,  B32B9/00 ,  B32B17/04 ,  B32B27/04 ,  B32B27/12 ,  B32B27/30 ,  C08J5/24 ,  C08J2363/00 ,  C08K3/36 ,  C08K7/14 ,  C09D4/00

    Abstract: Disclosed herein are dual cure compositions, methods to cure dual cure compositions, the dual cure compositions comprising at least one filler, at least one curable monomer comprising at least one of an ethylenic unit or cyclic ether unit or mixture thereof; at least one photoinitiator; and at least one thermal initiator. The method comprises the step of photocuring by exposing the compositions to radiation to at least partially photocure the composition, which in turn generates an exotherm which initiates thermal curing. The methods may be used to make cured thick compositions and sandwich structures. Articles made by the methods are also described.

    Abstract translation: 本文公开了双重固化组合物，固化双重固化组合物的方法，所述双重固化组合物包含至少一种填料，至少一种包含烯属单元或环醚单元或其混合物中的至少一种的可固化单体; 至少一种光引发剂; 和至少一种热引发剂。 该方法包括通过将组合物暴露于辐射以至少部分地光固化组合物而进行光固化的步骤，其又产生引发热固化的放热。 该方法可用于制备固化的厚组合物和夹心结构。 还描述了由方法制成的文章。

    Mixed tuned hybrid blade related method
    4.
    发明申请
    Mixed tuned hybrid blade related method 失效
    混合混合刀片相关方法

    公开(公告)号：US20060029501A1

    公开(公告)日：2006-02-09

    申请号：US10913407

    申请日：2004-08-09

    Applicant: Steven Burdgick ,  Guy DeLeonardo ,  Wendy Lin ,  Kevin Barb

    Inventor： Steven Burdgick ,  Guy DeLeonardo ,  Wendy Lin ,  Kevin Barb

    IPC: B64C27/46

    CPC classification number: F01D5/147 ,  F01D5/16 ,  F05D2300/43 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

    Abstract: A steam turbine blade includes a shank portion and an airfoil portion. The airfoil portion is formed with at least one pocket filled with a polymer filler material chosen as a function of natural frequency impact on the turbine blade or as a function of the damping characteristics of the filler materials. A steam turbine rotor wheel includes a plurality of blades secured about a circumferential periphery of the wheel, each blade having one or more pockets in the airfoil portion, the plurality of blades divided into two groups of blades. The pockets of one group of blades are filled with one or more polymer filler materials, and the pockets of the other group of blades filled with one or more polymer filler materials, wherein the polymer filler materials in the one group of blades creates different natural frequencies or damping characteristics in the blades of the one group than the polymer filler materials in the blades of the other group. The two groups of blades are assembled on the rotor wheel in accordance with a predetermined pattern.

    Abstract translation: 蒸汽轮机叶片包括柄部和翼型部。 机翼部分形成有至少一个填充有聚合物填充材料的袋，该聚合物填充材料根据对涡轮叶片的固有频率冲击而变化，或者作为填充材料的阻尼特性的函数。 蒸汽轮机转子轮包括围绕车轮的圆周周围固定的多个叶片，每个叶片在翼型部分中具有一个或多个袋，多个叶片被分成两组叶片。 一组叶片的口袋填充有一种或多种聚合物填充材料，另一组叶片的袋填充有一种或多种聚合物填料材料，其中一组叶片中的聚合物填料材料产生不同的固有频率 或阻尼特性比在另一组的叶片中的聚合物填充材料的阻力特性。 两组叶片根据预定图案组装在转子轮上。

    Epoxy polymer precursors and epoxy polymers resistant to damage by high-energy radiation
    5.
    发明申请
    Epoxy polymer precursors and epoxy polymers resistant to damage by high-energy radiation 审中-公开
    环氧聚合物前体和耐高能辐射损伤的环氧聚合物

    公开(公告)号：US20050107580A1

    公开(公告)日：2005-05-19

    申请号：US10971393

    申请日：2004-10-25

    Applicant: Sean Armstrong ,  Wendy Lin ,  Alan Kasner

    Inventor： Sean Armstrong ,  Wendy Lin ,  Alan Kasner

    IPC: G01T1/20 ,  C08G59/18 ,  C08G59/40 ,  C08G59/42 ,  C08G59/50 ,  C08L63/00

    CPC classification number: C08G59/50 ,  C08G59/18 ,  C08G59/42 ,  C08L63/00 ,  C08L2666/20

    Abstract: Epoxy polymer precursors and epoxy polymers resulting therefrom are tolerant to bombardment by high-energy radiation. The epoxy polymer precursors comprise at least an epoxy resin free of aromatic units and at least a curing agent selected from the group consisting of aliphatic polyamines, cycloaliphatic polyamines, polyamides, aliphatic anhydrides, cycloaliphatic anhydrides, and mixtures thereof. In one embodiment of the invention the epoxy resin comprises at least a cycloparaffinic group, and the curing agent comprises a polyamine derived from cyclohexane. Such epoxy polymer compositions are used to form reflectors elements between adjacent scintillator elements in high-energy radiation detector array.

    Abstract translation: 由此产生的环氧聚合物前体和环氧聚合物可耐受高能辐射的轰击。 环氧聚合物前体至少包含不含芳族单元的环氧树脂和至少一种选自脂族多胺，脂环族多胺，聚酰胺，脂族酸酐，脂环族酸酐及其混合物的固化剂。 在本发明的一个实施方案中，环氧树脂至少包含环烷烃基，并且固化剂包含衍生自环己烷的多胺。 这种环氧聚合物组合物用于在高能辐射探测器阵列中在相邻闪烁体元件之间形成反射器元件。

    Joining of composite materials by induction heating
    6.
    发明授权
    Joining of composite materials by induction heating 失效
    通过感应加热连接复合材料

    公开(公告)号：US5240542A

    公开(公告)日：1993-08-31

    申请号：US579379

    申请日：1990-09-06

    Applicant: Alan K. Miller ,  Wendy Lin

    Inventor： Alan K. Miller ,  Wendy Lin

    IPC: B23K13/01 ,  B29C65/00 ,  B29C65/36

    CPC classification number: B29C66/836 ,  B23K13/015 ,  B29C65/3616 ,  B29C65/3684 ,  B29C65/3696 ,  B29C66/3474 ,  B29C66/349 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/81261 ,  B29C66/81262 ,  B29C66/81811 ,  B29C65/3668 ,  B29C66/71 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/8122 ,  B29L2031/3076 ,  B29L2031/3085

    Abstract: Two pieces of composite material are simultaneously joined together throughout an interface between the two pieces, by induction heating the interface region with an induction coil placed, at least in part, adjacent to the bonding region, and forcing the composite material at the interface together while heating. The approach is particularly useful in joining pieces having "long interfaces" whose longitudinal dimension is substantially larger than its transverse dimension, for example the long interfaces between aircraft wing stiffeners and skins. The induction coil is configured so that, at any one longitudinal location along the interface, the primary current flowing therethrough does not flow in opposite directions in the portions of the coil overlying the interface, and preferably flows in substantially the same direction throughout the interface. Unheated "cold spots" in the interface being bonded, which would not bond properly, are thereby avoided. An electrically nonconductive but thermally conductive material may be placed between the induction coil and the composite material pieces to act as both a heat sink and a pressure-applying tool. Bonding may be enhanced by placing a susceptor made of the same materials as the composite materials being bonded but having a higher electrical conductivity, in the interface between the two composite material pieces prior to induction heating.

    Abstract translation: 两片复合材料同时通过两片之间的界面连接在一起，通过感应加热该界面区域，该感应线圈至少部分地放置在与接合区域相邻的感应线圈上，并且将该界面处的复合材料强制加在一起，同时 加热。 该方法在连接具有纵向尺寸基本上大于其横向尺寸的“长接口”的部件中是特别有用的，例如飞机机翼加强件和皮肤之间的长接口。 感应线圈构造成使得在沿着界面的任何一个纵向位置处，流过其中的一次电流不会在覆盖界面的线圈的部分中沿相反方向流动，并且优选地在整个界面上沿基本相同的方向流动。 因此避免了不能正确粘合的界面中未加热的“冷点”。 可以在感应线圈和复合材料片之间放置不导电但导热材料，以充当散热器和压力施加工具。 通过在感应加热之前在两个复合材料片之间的界面中放置由与待结合的复合材料相同的材料制成的基座，但具有较高的导电性，可以增强接合。

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