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    TURBINE BLADE WITH AIRFOIL TIP HAVING CUTTING TIPS
    4.
    发明申请
    TURBINE BLADE WITH AIRFOIL TIP HAVING CUTTING TIPS 审中-公开
    涡轮叶片带有空气带提示切割提示

    公开(公告)号：US20150078900A1

    公开(公告)日：2015-03-19

    申请号：US14031457

    申请日：2013-09-19

    申请人： David B. Allen

    发明人： David B. Allen

    IPC分类号： F01D5/20

    CPC分类号： F01D5/20 ,  F01D11/122 ,  F05D2250/21 ,  F05D2250/221

    摘要： A turbine blade having a squealer tip at a radially outer end of the turbine blade with a plurality of abradable coating cutting tips extending radially therefrom toward a ring segment is disclosed. During operation, the abradable coating cutting tips may cut into an abradable coating on the ring segments of the turbine engine that are positioned radially outward from the turbine blade. The plurality of abradable coating cutting tips may include one or more cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.

    摘要翻译： 公开了一种涡轮叶片，其具有在涡轮机叶片的径向外端处的尖叫尖端，其具有从其径向延伸到环段的多个可磨损涂层切割尖端。 在操作期间，可磨损的涂层切割尖端可以被切割成涡轮发动机的环段上的可磨损涂层，其从涡轮叶片径向向外定位。 多个可磨损的涂层切割尖端可以包括一个或多个切割区域，该切割区域从尖叫尖端延伸到至少一个可磨损涂层切割尖端的最外端。

    Method of measuring coating thickness using infrared light
    5.
    发明授权
    Method of measuring coating thickness using infrared light 有权
    使用红外光测量涂层厚度的方法

    公开(公告)号：US08300232B2

    公开(公告)日：2012-10-30

    申请号：US12543674

    申请日：2009-08-19

    申请人： David G. Sansom ,  David B. Allen ,  Anirudha Vaidya

    发明人： David G. Sansom ,  David B. Allen ,  Anirudha Vaidya

    IPC分类号： G01B9/02 ,  G01B11/02 ,  G01B11/28

    CPC分类号： G01B11/0616

    摘要： A method of measuring a thickness of a coating on a substrate material. A first pulse of monochromatic light having a predetermined first wavelength is emitted toward the coating and substrate material. A second pulse of monochromatic light having a predetermined second wavelength is emitted toward the coating and substrate material, the second wavelength being different than the first wavelength. A first elapsed time is measured from emission of the first pulse of light to reception of a reflection of the first pulse of light from a surface of the substrate material at an interface with the coating. A second elapsed time is measured from emission of the second pulse of light to reception of a reflection of the second pulse of light from an outer surface of the coating. A thickness of the coating is determined as a function of a difference between the first and second elapsed times.

    摘要翻译： 测量衬底材料上的涂层厚度的方法。 具有预定第一波长的单色光的第一脉冲朝向涂层和基底材料发射。 具有预定第二波长的单色光的第二脉冲朝向涂层和基板材料发射，第二波长不同于第一波长。 从第一脉冲光的发射到在与涂层的界面处接收来自基板材料的表面的第一脉冲光的反射测量第一经过时间。 从第二脉冲光的发射到接收来自涂层的外表面的第二脉冲光的反射测量第二经过时间。 根据第一和第二经过时间之间的差异确定涂层的厚度。

    Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine
    6.
    发明授权
    Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine 有权
    可滑动的弹簧加载的过渡到涡轮密封装置和热屏蔽系统，包括在燃气涡轮发动机的过渡/涡轮连接处的密封件

    公开(公告)号：US07784264B2

    公开(公告)日：2010-08-31

    申请号：US11498478

    申请日：2006-08-03

    申请人： Adam J. Weaver ,  Raymond S. Nordlund ,  David B. Allen ,  Daniel O. Davies

    发明人： Adam J. Weaver ,  Raymond S. Nordlund ,  David B. Allen ,  Daniel O. Davies

    IPC分类号： F04D29/04 ,  F23R3/42

    CPC分类号： F01D9/023 ,  F01D11/005 ,  F02C7/28

    摘要： One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second, generally C-shaped section (301). The generally C-shaped section (301) comprises a flattened portion (305) near the first, flattened section (302), and a curved portion (306) extending to a free edge (307). A fiber metal strip component (309) may be attached to the flattened portion (305) to define a first engagement surface adapted to engage an upstream side (336) of an outer vane seal rail (337), and a second engagement surface 308, adjacent the free edge (307), provides an opposed wear surface adapted to engage a downstream side (338) of the outer vane seal rail (337). System embodiments also are described, in which such transition-to-turbine seal (300) is isolated from a hot gas path (350) by provision of a plurality of cooling apertures (327) in the transition (325).

    摘要翻译： 过渡到涡轮机密封件（300）的一个实施例包括适于容纳在过渡（325）的周向轴向槽（320）中的第一平坦部分（302），以及第二大致C形截面 （301）。 大致C形截面（301）包括靠近第一平坦部分（302）的平坦部分（305）和延伸到自由边缘（307）的弯曲部分（306）。 纤维金属带部件（309）可以附接到平坦部分（305）以限定适于接合外部叶片密封轨道（337）的上游侧（336）的第一接合表面，以及第二接合表面308， 邻近自由边缘（307），提供适于接合外部叶片密封轨道（337）的下游侧（338）的相对的磨损表面。 还描述了系统实施例，其中通过在过渡（325）中设置多个冷却孔（327），这种过渡到涡轮机密封件（300）与热气体路径（350）隔离。

    Coating system
    7.
    发明申请
    Coating system 审中-公开
    涂装系统

    公开(公告)号：US20090123722A1

    公开(公告)日：2009-05-14

    申请号：US11983373

    申请日：2007-11-08

    申请人： David B. Allen ,  Eckart Schumann ,  Ramesh Subramanian

    发明人： David B. Allen ,  Eckart Schumann ,  Ramesh Subramanian

    IPC分类号： B32B3/26

    CPC分类号： C23C28/042 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/005 ,  Y02T50/67 ,  Y10T428/249953

    摘要： The invention relates to a coating system (2) for a component (1) which comprises a porous layer (3) and an abradable layer (4) on the porous layer (3). Further the invention relates to an assembly of two components (1) which are relatively movable to each other and form a gap in between. One component (1) is provided with a coating system (2) and the other component (1) is in sliding contact with the coating system (2).

    摘要翻译： 本发明涉及一种用于组分（1）的涂料体系（2），其包括多孔层（3）上的多孔层（3）和耐磨层（4）。 此外，本发明涉及两个组件（1）的组件，它们彼此相对移动并在其间形成间隙。 一个部件（1）设置有涂层系统（2），另一部件（1）与涂层系统（2）滑动接触。

    ABRASIVE COATED PREFORM FOR A TURBINE BLADE TIP
    8.
    发明申请
    ABRASIVE COATED PREFORM FOR A TURBINE BLADE TIP 失效
    用于涡轮叶片的磨料涂层预制件

    公开(公告)号：US20120051934A1

    公开(公告)日：2012-03-01

    申请号：US12870997

    申请日：2010-08-30

    申请人： David B. Allen

    发明人： David B. Allen

    IPC分类号： F01D5/14 ,  B23P15/02

    CPC分类号： F01D5/20 ,  C25D5/50 ,  C25D7/10 ,  F01D11/122 ,  F05B2280/20082 ,  F05D2250/221

    摘要： A squealer tip preform having a coating including an abrasive is disclosed. The squealer tip may be separately formed from a generally elongated blade to which the squealer tip preform is configured to be attached. The squealer tip may be configured such that an outer surface of the squealer tip preform is generally aligned with an outer side surface of the turbine blade defining a cross-sectional profile of the turbine blade. Forming the squealer tip preform with an abrasive coating separate from the turbine blade greatly reduces costs and improves efficiency as compared with conventional systems.

    摘要翻译： 公开了一种具有包括磨料的涂层的尖叫尖端预制件。 尖叫尖端可以与通常细长的刀片分开地形成，所述尖叫尖端预制件被配置成附接到刀片。 尖叫尖端可以被配置成使得鸣叫器尖端预制件的外表面大致与涡轮叶片的外侧表面对准，其限定涡轮叶片的横截面轮廓。 与传统系统相比，形成具有与涡轮机叶片分离的研磨涂层的尖叫嘴预制件大大降低了成本并提高了效率。

    Sprayed weld strip for improved weldability
    9.
    发明申请
    Sprayed weld strip for improved weldability 失效
    喷涂焊接条可提高焊接性

    公开(公告)号：US20080166585A1

    公开(公告)日：2008-07-10

    申请号：US11649574

    申请日：2007-01-04

    申请人： David B. Allen ,  Allister W. James ,  David W. Hunt

    发明人： David B. Allen ,  Allister W. James ,  David W. Hunt

    IPC分类号： B32B15/01 ,  B23K1/20 ,  B23K20/00 ,  B23K31/02 ,  B23K9/167

    CPC分类号： B23K9/0026 ,  B23K9/167 ,  B23K9/23 ,  B23K9/235 ,  B23K2103/18 ,  B23K2103/26 ,  Y10T428/12493

    摘要： A method for welding to a superalloy material without causing cracking of the material. The method includes the steps of depositing a weld strip (18) of a weldable material onto a superalloy substrate material (12) using a spray deposition process (20) and then forming a weldment (26) to the weld strip. None or a controlled amount of the substrate material (12) is melted during the weld in order to maintain the concentration of strengthening elements in the local melt within a zone of weldability. The spray deposition process may be a thermal process such as HVOF or a cold spray process. A groove (16) may be formed in a surface (10) of the superalloy substrate material to receive the weld strip. A diffusion heat treatment step may be used to improve adhesion between the weld strip and the superalloy material.

    摘要翻译： 焊接到超合金材料而不引起材料开裂的方法。 该方法包括以下步骤：使用喷雾沉积工艺（20）将焊接材料的焊接条（18）沉积到超合金基底材料（12）上，然后形成焊接条（26）。 在焊接期间没有或受控量的基底材料（12）熔化，以便将局部熔体中的强化元素的浓度保持在可焊性区域内。 喷雾沉积工艺可以是诸如HVOF或冷喷涂工艺的热处理。 可以在超合金基底材料的表面（10）中形成凹槽（16）以接收焊接条。 可以使用扩散热处理步骤来改善焊接条和超合金材料之间的粘附。

    Superalloy material with improved weldability
    10.
    发明授权
    Superalloy material with improved weldability 有权
    具有改善焊接性能的超合金材料

    公开(公告)号：US06696176B2

    公开(公告)日：2004-02-24

    申请号：US10092326

    申请日：2002-03-06

    申请人： David B. Allen ,  Gregg P. Wagner ,  Brij B. Seth

    发明人： David B. Allen ,  Gregg P. Wagner ,  Brij B. Seth

    IPC分类号： B32B1501

    CPC分类号： C22C19/055 ,  B23K35/304 ,  B23K35/3046 ,  Y10T428/12931 ,  Y10T428/12937 ,  Y10T428/12944

    摘要： A fusion weldable superalloy containing 0.005-0.5 wt. % scandium. In one embodiment, the superalloy may have a composition similar to IN-939 alloy, but having added scandium and having only 0.005-0.040 wt. % zirconium. A gas turbine component may be formed by an investment casting of such a scandium-containing superalloy, and may include a fusion weld repaired area. A scandium-containing nickel-based superalloy coated with an MCrAlY bond coat will have improved cyclic oxidation resistance due to the sulfur-gettering effect of the scandium.

    摘要翻译： 一种熔融焊接的超合金，其含有0.005-0.5wt。 ％钪。 在一个实施方案中，超合金可以具有类似于IN-939合金的组成，但是添加钪并且仅具有0.005-0.040wt。 ％锆。 燃气轮机部件可以通过这种含钪的超级合金的熔模铸造形成，并且可以包括熔焊修补区域。 涂覆有MCrAlY粘合涂层的含钪镍基超合金由于钪的吸硫作用而具有改善的环氧化抗性。