利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

10 条记录 (耗时 0.017 秒)

    COATING SYSTEMS CONTAINING GAMMA-PRIME NICKEL ALUMINIDE COATING
    2.
    发明申请
    COATING SYSTEMS CONTAINING GAMMA-PRIME NICKEL ALUMINIDE COATING 有权
    包含GAMMA-PRIME镍铬铝涂料的涂料体系

    公开(公告)号：US20060093850A1

    公开(公告)日：2006-05-04

    申请号：US10904220

    申请日：2004-10-29

    申请人： Ramgopal Darolia ,  Joseph Rigney ,  William Walston

    发明人： Ramgopal Darolia ,  Joseph Rigney ,  William Walston

    IPC分类号： B32B15/01 ,  B32B15/04

    CPC分类号： F01D5/288 ,  F05C2201/0466 ,  F05D2230/90 ,  F05D2300/611 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12875 ,  Y10T428/12931 ,  Y10T428/12937 ,  Y10T428/12944

    摘要： An overlay coating for articles used in hostile thermal environments. The coating has a predominantly gamma prime-phase nickel aluminide (Ni3Al) composition suitable for use as an environmental coating and as a bond coat for a thermal barrier coating. The coating has a composition of, by weight, at least 6% to about 15% aluminum, about 2% to about 5% chromium, optionally one or more reactive elements in individual or combined amounts of up to 4%, optionally up to 2% silicon, optionally up to 60% of at least one platinum group metal, and the balance essentially nickel. A thermal-insulating ceramic layer may be deposited on the coating.

    摘要翻译： 用于敌对热环境中的物品的覆盖涂层。 该涂层主要具有适合用作环境涂层和用作热障涂层的粘合涂层的γ初始相铝酸镍（Ni 3 Al 3 Al）组合物。 该涂层具有按重量计至少6％至约15％的铝，约2％至约5％的铬，任选的一种或多种反应性元素的组合物，其个体或组合量可达4％，任选至多2 ％硅，任选至多60％的至少一种铂族金属，余量基本上为镍。 绝热陶瓷层可以沉积在涂层上。

    SUPERALLOY ARTICLE HAVING A GAMMA-PRIME NICKEL ALUMINIDE COATING
    4.
    发明申请
    SUPERALLOY ARTICLE HAVING A GAMMA-PRIME NICKEL ALUMINIDE COATING 有权
    具有优质镍基铝涂料的超级合金制品

    公开(公告)号：US20060093851A1

    公开(公告)日：2006-05-04

    申请号：US10904222

    申请日：2004-10-29

    申请人： Ramgopal Darolia ,  William Walston

    发明人： Ramgopal Darolia ,  William Walston

    IPC分类号： F03B3/12 ,  B32B15/01

    CPC分类号： C23C28/321 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/611 ,  Y02T50/671 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12875 ,  Y10T428/12931 ,  Y10T428/12937 ,  Y10T428/12944

    摘要： An article for use in hostile thermal environments, such as a component of a gas turbine engine. The article includes a nickel-base superalloy substrate that is prone to formation of a deleterious secondary reaction zone (SRZ), and an overlay coating having a predominantly gamma prime-phase nickel aluminide (Ni3Al) composition suitable for use as an environmental coating, including a bond coat for a thermal barrier coating. The coating comprises a chromium-containing nickel aluminide intermetallic overlay coating of predominantly the gamma prime phase, in which aluminum is present in the coating in an amount approximately equal to the aluminum content of the superalloy substrate so as to inhibit diffusion of aluminum from the overlay coating into the superalloy substrate.

    摘要翻译： 用于敌对热环境中的物品，例如燃气轮机的部件。 该制品包括易于形成有害的次级反应区（SRZ）的镍基超级合金基材和具有主要为γ原相镍铝化合物（Ni 3 Al 3 Al）组成的覆盖涂层 适合用作环境涂层，包括用于热障涂层的粘合涂层。 该涂层包括主要为γ'相的含铬镍铝金属间覆盖涂层，其中铝在涂层中的含量约等于超级合金基材的铝含量，从而抑制铝从覆盖层的扩散 涂覆到超合金基材中。

    NICKEL-BASE SUPERALLOY
    5.
    发明申请
    NICKEL-BASE SUPERALLOY 审中-公开
    镍基超级合金

    公开(公告)号：US20070044869A1

    公开(公告)日：2007-03-01

    申请号：US11162221

    申请日：2005-09-01

    申请人： Ramgopal Darolia ,  William Walston ,  Kevin O'Hara

    发明人： Ramgopal Darolia ,  William Walston ,  Kevin O'Hara

    IPC分类号： C22C19/05

    CPC分类号： C22C19/057 ,  C22F1/10 ,  C30B29/52

    摘要： A nickel-base alloy that exhibits a desirable balance of mechanical properties, environmental properties, and microstructural stability suitable for gas turbine engine applications. The nickel-base alloy is in the form of a single-crystal casting consisting of, by weight, 5.75% to 6.5% aluminum, 4% to 5% tantalum, 2% to 6% chromium, 5.5% to 7% tungsten, 1.5% to 3% molybdenum, 4% to 5% rhenium, up to 1.0% niobium, 10% to 16% cobalt, up to 1% titanium, 0.01% to 0.05% carbon, up to 0.005% boron, up to 0.01% yttrium, 0.5% to 1.0% hafnium, the balance nickel and incidental impurities. The alloy has a density of not more than 0.320 lbs/in3 (about 8.87 g/cm3), and contains a combined amount of aluminum, tungsten, molybdenum, niobium, titanium, and hafnium specified relative to the combined amount of tantalum and rhenium.

    摘要翻译： 表现出适合燃气轮机发动机应用的机械性能，环境特性和微观结构稳定性所需平衡的镍基合金。 镍基合金为单晶铸造，其重量为5.75％至6.5％的铝，4％至5％的钽，2％至6％的铬，5.5％至7％的钨，1.5 ％至3％的钼，4％至5％的铼，至多1.0％的铌，10％至16％的钴，至多1％的钛，0.01％至0.05％的碳，至多0.005％的硼，至多0.01％的钇 ，0.5〜1.0％的铪，余量为镍和杂质。 该合金的密度不超过0.320磅/平方英寸（约8.87克/立方厘米），并含有铝，钨，钼，铌的组合量 ，钛和铪，相对于钽和铼的组合量而言。

    Stable, high-temperature nickel-base superalloy and single-crystal articles utilizing the superalloy
    6.
    发明申请
    Stable, high-temperature nickel-base superalloy and single-crystal articles utilizing the superalloy 审中-公开
    稳定的高温镍基超级合金和采用超级合金的单晶制品

    公开(公告)号：US20060039820A1

    公开(公告)日：2006-02-23

    申请号：US10922510

    申请日：2004-08-20

    申请人： Ramgopal Darolia ,  William Walston ,  Kevin O'Hara ,  Christine Govern

    发明人： Ramgopal Darolia ,  William Walston ,  Kevin O'Hara ,  Christine Govern

    IPC分类号： C22C19/05

    CPC分类号： C22C19/057 ,  C23C28/322 ,  C23C28/3455 ,  F01D5/28 ,  F01D25/005 ,  F05D2300/607 ,  Y02T50/67 ,  Y02T50/671

    摘要： An article includes a substantially single crystal piece having a composition consisting essentially of, in weight percent, from 0.4 to 6.5 percent ruthenium, from 3 to 8 percent rhenium, from 5.8 to 10.7 percent tantalum, from 4.25 to 17.0 percent cobalt, from 0.1 to 2.0 percent hafnium, from 0.02 to 0.4 percent carbon, from 0.001 to 0.005 percent boron, from 0 to 0.02 percent yttrium, from 1 to 4 percent molybdenum, from 1.25 to 10 percent chromium, from 0.5 to 2.0 percent niobium, from 0.05 to 0.5 percent zirconium, from 5.0 to 6.6 percent aluminum, from 0 to 2.0 percent titanium, from 3.0 to 7.5 percent tungsten, and from 0.1 to 6 percent of platinum, iridium, rhodium, and palladium, and combinations thereof, balance nickel and incidental impurities.

    摘要翻译： 一种制品包括基本上单晶片，其组成基本上由重量百分比组成，钌含量为henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium henium r r r r r r r r r r r r r r r 2.0％的铪，0.02〜0.4％的碳，0.001〜0.005％的硼，0〜0.02％的钇，1〜4％的钼，1.25〜10％的铬，0.5〜2.0％的铌，0.05〜0.5 的锆，5.0至6.6％的铝，0至2.0％的钛，3.0至7.5％的钨和0.1至6％的铂，铱，铑和钯及其组合，才能平衡镍和杂质。

    Aluminide coating of turbine engine component
    7.
    发明申请
    Aluminide coating of turbine engine component 失效
    涡轮发动机部件的铝酸盐涂层

    公开(公告)号：US20050008780A1

    公开(公告)日：2005-01-13

    申请号：US10615094

    申请日：2003-07-08

    申请人： John Ackerman ,  Michael Weimer ,  Joseph Heaney ,  William Walston ,  Bangalore Nagaraj

    发明人： John Ackerman ,  Michael Weimer ,  Joseph Heaney ,  William Walston ,  Bangalore Nagaraj

    IPC分类号： C23C10/08 ,  C23C16/04 ,  C23C16/20 ,  C23C16/56 ,  C23C16/00

    CPC分类号： C23C16/56 ,  C23C10/08 ,  C23C16/045 ,  C23C16/20 ,  Y02T50/67

    摘要： A method for forming an aluminide coating on a turbine engine component having an external surface and an internal cavity defined by an internal surface that is connected to the external surface by at least one hole. The method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; flowing a tri-alkyl aluminum coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum coating on the external and internal surfaces of the component; and heating the component in a nonoxidizing atmosphere at a specified temperature and time to form an aluminide coating on the external and internal surfaces. The coated component is typically then maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the external and internal surfaces of the component. In one embodiment, the turbine engine component is a turbine engine blade having an external surface and an internal cooling cavity having an internal surface that is connected to the external surface by cooling holes.

    摘要翻译： 一种用于在涡轮发动机部件上形成铝化物涂层的方法，所述方法具有外表面和由内表面限定的内腔，所述内表面通过至少一个孔连接到所述外表面。 该方法在具有中空的内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与待涂覆的部件装载; 在特定温度，压力和时间下将三烷基铝涂层气体流入装载的涂覆室中，以将铝涂层沉积在部件的外表面和内表面上; 并在特定温度和时间下在非氧化气氛中加热组分，以在外表面和内表面上形成铝化物涂层。 然后将涂覆的组分在氧的存在下保持在升高的温度，以在组件的外表面和内表面上形成氧化物涂层。 在一个实施例中，涡轮发动机部件是具有外表面和内部冷却腔的涡轮发动机叶片，其具有通过冷却孔连接到外表面的内表面。

    Method for selecting a reduced-tantalum superalloy composition of matter and article made therefrom
    8.
    发明申请
    Method for selecting a reduced-tantalum superalloy composition of matter and article made therefrom 审中-公开
    用于选择物质的还原钽超合金组合物和由其制成的制品的方法

    公开(公告)号：US20050139295A1

    公开(公告)日：2005-06-30

    申请号：US10812628

    申请日：2004-03-29

    申请人： Kevin O'Hara ,  William Walston ,  Earl Ross

    发明人： Kevin O'Hara ,  William Walston ,  Earl Ross

    IPC分类号： F01D5/28 ,  C22C19/05 ,  F01D25/00 ,  F02C7/00

    CPC分类号： C22C19/057

    摘要： A superalloy article has a composition consisting essentially of, in weight percent, from about 4 to about 12 percent cobalt, from about 3.5 to about 7 percent tungsten, from about 2 to about 9 percent chromium, from about 0.5 to about 4.5 percent tantalum, from about 5.5 to about 7.5 percent aluminum, from 0 to about 5.5 percent rhenium, from about 0.1 to about 1.2 percent titanium, from 0 to about 3 percent molybdenum, from 0 to about 3 percent ruthenium, from about 0.5 to about 2 percent columbium, about 0.01 percent maximum boron, about 0.07 percent maximum carbon, from about 0.3 to about 1 percent hafnium, about 0.01 percent maximum zirconium, about 0.03 percent maximum yttrium, from 0 to about 0.5 percent vanadium, about 0.01 percent maximum cerium, and about 0.01 percent maximum lanthanum, balance nickel and impurity elements. The article is preferably substantially a single crystal or oriented polycrystal in a shape such as a gas turbine blade.

    摘要翻译： 超级合金制品具有以重量百分比计约4至约12％的钴，约3.5至约7％的钨，约2至约9％的铬，约0.5至约4.5％的钽， 约5.5至约7.5％的铝，0至约5.5％的铼，约0.1至约1.2％的钛，0至约3％的钼，0至约3％的钌，约0.5％至约2％的铌 ，约0.01％的最大硼，约0.07％的最大碳，约0.3％至约1％的铪，约0.01％的最大锆，约0.03％的最大钇，0％至约0.5％的钒，约0.01％的最大铈和约 0.01％的最大镧，余量为镍和杂质元素。 该制品优选地基本上是诸如燃气轮机叶片的形状的单晶或取向多晶体。

    THERMAL BARRIER COATING AND PROCESS THEREFOR
    9.
    发明申请
    THERMAL BARRIER COATING AND PROCESS THEREFOR 失效
    热障涂层及其工艺

    公开(公告)号：US20060280926A1

    公开(公告)日：2006-12-14

    申请号：US11160164

    申请日：2005-06-10

    申请人： Irene Spitsberg ,  Brett Boutwell ,  Robert Bruce ,  Curtis Johnson ,  Bangalore Nagaraj ,  William Walston

    发明人： Irene Spitsberg ,  Brett Boutwell ,  Robert Bruce ,  Curtis Johnson ,  Bangalore Nagaraj ,  William Walston

    IPC分类号： B32B3/26 ,  B32B3/06

    CPC分类号： C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  Y10T428/249953 ,  Y10T428/249955

    摘要： A thermal barrier coating and deposition process for a component intended for use in a hostile thermal environment, such as the turbine, combustor and augmentor components of a gas turbine engine. The TBC has a first coating portion on at least a first surface portion of the component. The first coating portion is formed of a ceramic material to have at least an inner region, at least an outer region overlying the inner region, and a columnar microstructure whereby the inner and outer regions comprise columns of the ceramic material. The columns of the inner region are more closely spaced than the columns of the outer region so that the inner region of the first coating portion is denser than the outer region of the first coating portion, wherein the higher density of the inner region promotes the impact resistance of the first coating portion.

    摘要翻译： 用于在敌对热环境中使用的部件的热障涂层和沉积工艺，例如燃气轮机的涡轮机，燃烧器和增压器部件。 所述TBC在所述部件的至少第一表面部分上具有第一涂覆部分。 第一涂覆部分由陶瓷材料形成，至少具有内部区域，至少覆盖内部区域的外部区域和柱状微结构，由此内部和外部区域包括陶瓷材料的列。 内部区域的列与外部区域的列紧密地间隔开，使得第一涂覆部分的内部区域比第一涂覆部分的外部区域更致密，其中内部区域的较高密度促进了冲击 第一涂布部分的电阻。