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74 条记录 (耗时 0.019 秒)

    Turbine engine component with cooling passages
    31.
    发明授权
    Turbine engine component with cooling passages 有权
    具有冷却通道的涡轮发动机部件

    公开(公告)号：US08096751B2

    公开(公告)日：2012-01-17

    申请号：US12183168

    申请日：2008-07-31

    申请人： Douglas J. Arrell ,  Allister W. James

    发明人： Douglas J. Arrell ,  Allister W. James

    IPC分类号： F01D5/14

    CPC分类号： F01D5/3061

    摘要： A component for use in a turbine engine including a first member and a second member associated with the first member. The second member includes a plurality of connecting elements extending therefrom. The connecting elements include securing portions at ends thereof that are received in corresponding cavities formed in the first member to attach the second member to the first member. The connecting elements are constructed to space apart a first surface of the second member from a first surface of the first member such that at least one cooling passage is formed between adjacent connecting elements and the first surface of the second member and the first surface of the first member.

    摘要翻译： 一种用于涡轮发动机的部件，包括第一构件和与第一构件相关联的第二构件。 第二构件包括从其延伸的多个连接元件。 连接元件包括在其端部处的固定部分，其接收在形成在第一构件中的相应空腔中，以将第二构件附接到第一构件。 连接元件被构造成使第二构件的第一表面与第一构件的第一表面分开，使得在相邻的连接元件和第二构件的第一表面之间形成至少一个冷却通道， 第一名成员

    TURBINE AIRFOIL WITH OUTER WALL THICKNESS INDICATORS
    32.
    发明申请
    TURBINE AIRFOIL WITH OUTER WALL THICKNESS INDICATORS 失效
    涡轮机空气外壁厚度指示器

    公开(公告)号：US20110299990A1

    公开(公告)日：2011-12-08

    申请号：US12794972

    申请日：2010-06-07

    申请人： John J. Marra ,  Allister W. James ,  Gary B. Merrill

    发明人： John J. Marra ,  Allister W. James ,  Gary B. Merrill

    IPC分类号： F01D5/14 ,  B22D23/00 ,  B23P15/02

    CPC分类号： B23P15/02 ,  B22C9/04 ,  B22C9/10 ,  F01D5/147 ,  F01D21/003 ,  Y10T29/49336

    摘要： A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.

    摘要翻译： 一种可用于涡轮发动机并且包括用于确定外壁叶片厚度的深度指示器的涡轮机翼型。 翼型件可以包括在外壁的外表面中具有多个凹槽的外壁。 凹槽可以具有表示外壁的期望外表面和壁厚的深度。 形成外壁的外表面的材料可以被去除以与每个凹槽中的最内点齐平，从而减小壁厚并提高效率。 多个槽可以定位在靠近尖端的翼型件的径向外部区域中。

    Oxidation resistant superalloy
    36.
    发明申请
    Oxidation resistant superalloy 审中-公开
    耐氧化超合金

    公开(公告)号：US20080260571A1

    公开(公告)日：2008-10-23

    申请号：US11788301

    申请日：2007-04-19

    申请人： Douglas J. Arrell ,  Allister W. James

    发明人： Douglas J. Arrell ,  Allister W. James

    IPC分类号： C22C19/05

    CPC分类号： C22C19/05

    摘要： A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is well-suited for components of gas or steam turbine engines including blades and vanes.

    摘要翻译： 公开了一种在氧化环境中形成氧化铬垢的镍基超级合金。 该合金在干燥或潮湿的气氛中在低于900℃的温度下提供良好的抗氧化性。 超级合金非常适合于包括叶片和叶片在内的气体或汽轮机发动机的部件。

    System for applying a continuous surface layer on porous substructures of turbine airfoils
    37.
    发明申请
    System for applying a continuous surface layer on porous substructures of turbine airfoils 有权
    在涡轮翼型的多孔子结构上施加连续表面层的系统

    公开(公告)号：US20080254276A1

    公开(公告)日：2008-10-16

    申请号：US11784982

    申请日：2007-04-10

    申请人： Allister W. James ,  Douglas J. Arrell

    发明人： Allister W. James ,  Douglas J. Arrell

    IPC分类号： B32B3/26 ,  B05D5/00

    CPC分类号： C23C24/08 ,  B22F7/002 ,  B22F7/06 ,  B22F2999/00 ,  C23C24/02 ,  F05B2230/40 ,  F05B2230/90 ,  F05C2253/14 ,  Y10T29/49337 ,  Y10T29/49982 ,  Y10T29/49993 ,  Y10T428/12042 ,  Y10T428/12451 ,  Y10T428/12479 ,  Y10T428/249953 ,  Y10T428/249957 ,  B22F3/15

    摘要： A system for forming a surface coating on an outer surface of a foam for use with cooling system of turbine engines. The system may include removing filler from the outer surface of the foam to expose a porous structure of the foam, whereby portions of the porous structure extend outwardly from a newly formed outer surface of the filler. A surface layer may be applied to the outer surface of the filler and exposed portions of the porous structure, whereby the surface layer is attached to the porous structure at least in part due to mechanical interaction with the portions of the porous structure extending outwardly from the newly formed outer surface of the filler. The filler material may then be removed from the porous structure.

    摘要翻译： 一种在泡沫的外表面上形成表面涂层以与涡轮发动机的冷却系统一起使用的系统。 该系统可以包括从泡沫的外表面去除填料以暴露泡沫的多孔结构，由此多孔结构的一部分从新形成的填料的外表面向外延伸。 可以将表面层施加到填料的外表面和多孔结构的暴露部分，由此表面层至少部分地由于与从多孔结构向外延伸的多孔结构的部分的机械相互作用而附接到多孔结构 新形成的填料外表面。 然后可以从多孔结构中去除填充材料。

    Sprayed weld strip for improved weldability
    39.
    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。

    Nickel alloy for turbine engine components
    40.
    发明授权
    Nickel alloy for turbine engine components 有权
    镍合金用于涡轮发动机部件

    公开(公告)号：US6132527A

    公开(公告)日：2000-10-17

    申请号：US206965

    申请日：1998-12-08

    申请人： Steven J Hessell ,  Wayne Voice ,  Allister W James ,  Sarah A Blackham ,  Colin J Small ,  Michael R Winstone

    发明人： Steven J Hessell ,  Wayne Voice ,  Allister W James ,  Sarah A Blackham ,  Colin J Small ,  Michael R Winstone

    IPC分类号： C22C19/05

    CPC分类号： C22C19/056

    摘要： A new nickel base superalloy suitable for compressor or turbine discs of gas turbine engines with fatigue crack propagation resistance equal to Waspaloy, tensile strength higher than Waspaloy and higher operating temperature than Waspaloy or UDIMET 720 family of alloys. The nickel base superalloy has a preferred composition by weight % of 14.0-19.0% cobalt, 14.35-15.15 Chromium, 4.25-5.25 Molybdenum, 1.35-2.15 tantalum, 3.45-4.15 titanium, 2.85-3.15 aluminium, 0.01-0.025 boron, 0.012-0.033 carbon, 0.05-0.07 zirconium, 0.5-1.0 hafnium, up to 1.0 rhenium, up to 2.0 tungsten, less than 0.5 niobium, up to 0.1 yttrium, up to 0.1 vanadium, up to 1.0 iron, up to 0.2 silicon, up to 0.15 manganese and balance nickel plus incidental impurities.

    摘要翻译： 一种新的镍基超级合金，适用于燃气轮机发动机的压缩机或涡轮盘，其疲劳裂纹扩展阻力等于Waspaloy，抗拉强度高于Waspaloy，工作温度高于Waspaloy或UDIMET 720系列合金。 镍基超级合金具有优选的组成重量百分比为14.0-19.0％的钴，14.35-15.15铬，4.25-5.25钼，1.35-2.15钽，3.45-4.15钛，2.85-3.15铝，0.01-0.025硼，0.012- 0.033碳，0.05-0.07锆，0.5-1.0铪，至多1.0铼，至多2.0钨，小于0.5铌，至多0.1钇，至多0.1钒，至多1.0铁，至多0.2硅，直至 0.15锰和平衡镍加附加杂质。