公开(公告)号：US20130337286A1

公开(公告)日：2013-12-19

申请号：US13881163

申请日：2011-10-19

Applicant: Friedhelm Schmitz ,  Werner Stamm

Inventor： Friedhelm Schmitz ,  Werner Stamm

IPC: C22C19/05 ,  C22C30/00 ,  B32B15/04

CPC classification number: C22C19/058 ,  B32B15/01 ,  B32B15/04 ,  C22C19/05 ,  C22C30/00 ,  C23C28/30 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05D2300/132 ,  F05D2300/15 ,  Y02T50/67 ,  Y02T50/6765 ,  Y10T428/12618

Abstract: Known protective coatings having a high Cr content, as well as silicon, have brittle phases that become additionally brittle under the influence of carbon during use. A protective coating is provided. The protective coating includes the composition of 24% to 26% cobalt, 10% to 12% aluminum, 0.2% to 0.5% yttrium, 12% to 14% chromium, and the remainder nickel.

Abstract translation: 具有高Cr含量的已知保护涂层以及硅，具有在使用期间在碳的影响下变得另外脆性的脆性相。 提供保护涂层。 保护涂层包括24％至26％的钴，10％至12％的铝，0.2％至0.5％的钇，12％至14％的铬以及其余的镍的组合物。

公开(公告)号：US08343573B2

公开(公告)日：2013-01-01

申请号：US12679389

申请日：2008-09-19

Applicant: Jens Dahl Jensen ,  Jens Klingemann ,  Ursus Krüger ,  Daniel Körtvelyessy ,  Volkmar Lüthen ,  Ralph Reiche ,  Oliver Stier

Inventor： Jens Dahl Jensen ,  Jens Klingemann ,  Ursus Krüger ,  Daniel Körtvelyessy ,  Volkmar Lüthen ,  Ralph Reiche ,  Oliver Stier

IPC: B05C13/00 ,  C23C4/08

CPC classification number: C23C30/00 ,  B22F5/04 ,  B22F7/08 ,  B23P6/007 ,  B23P6/045 ,  C23C24/04 ,  F01D5/005 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/40 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/2112 ,  F05D2300/2118

Abstract: A method for repairing a component such as a turbine blade is provided. At the end of its operating time, the component has, for example, a depletion of aluminium in a region near the surface. The application of a repair layer is provided including particles with an increased proportion of aluminium. A subsequent heat treatment may achieve the effect of equalizing the concentration of aluminium between the repair layer and the region near the surface, and so the aluminium content required for new components is achieved again.

Abstract translation: 提供了一种用于修理诸如涡轮叶片的部件的方法。 在其运行时间结束时，组件例如在靠近表面的区域中铝的消耗。 提供了修复层的应用，包括具有增加的铝比例的颗粒。 随后的热处理可以实现使修复层和表面附近的区域之间的铝浓度相等的效果，因此再次实现新组分所需的铝含量。

公开(公告)号：US20120099978A1

公开(公告)日：2012-04-26

申请号：US13147686

申请日：2010-02-04

Applicant: Roman Beyer ,  Boris Bublath ,  Ingo Just ,  Thomas Podgorski

Inventor： Roman Beyer ,  Boris Bublath ,  Ingo Just ,  Thomas Podgorski

IPC: F01D25/00 ,  B23P17/00

CPC classification number: F01D5/288 ,  B23P15/04 ,  B23P2700/06 ,  C23C28/00 ,  C23C28/022 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/284 ,  F01D5/286 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2240/90 ,  F05D2300/11 ,  F05D2300/15 ,  F05D2300/607 ,  F23R3/06 ,  F23R2900/00018 ,  Y02T50/67 ,  Y02T50/675 ,  Y10T29/49229

Abstract: Turbine components are often shipped individually and are not shipped assembled into a turbine. To this end, the turbine blade has to be protected of external stresses and external damage. This is done by an easily removable protective coating that easily evaporates during the first operation of the newly produced or restored component, so that the protective coating does not have to be removed in an additional operational step before installation.

Abstract translation: 涡轮机组件通常是单独运输的，没有运输组装到涡轮机中。 为此，涡轮机叶片必须受到外部应力和外部损坏的保护。 这是通过易于移除的保护涂层完成的，其在新生产或恢复的部件的第一次操作期间容易蒸发，使得在安装之前不需要在额外的操作步骤中去除保护涂层。

公开(公告)号：US07837440B2

公开(公告)日：2010-11-23

申请号：US11160272

申请日：2005-06-16

Applicant: Ronald S. Bunker ,  Gary Michael Itzel

Inventor： Ronald S. Bunker ,  Gary Michael Itzel

IPC: F01D5/08

CPC classification number: F01D5/20 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

Abstract: A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side.

Abstract translation: 用于涡轮机桶的顶盖件。 尖端盖可以包括冷侧和位于冷侧的多个销。

公开(公告)号：US20100028711A1

公开(公告)日：2010-02-04

申请号：US12181422

申请日：2008-07-29

Applicant: David A. Helmick ,  David Leslie Burin

Inventor： David A. Helmick ,  David Leslie Burin

IPC: B21D39/00

CPC classification number: F01D5/288 ,  C23C4/11 ,  C23C4/18 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/11 ,  F05D2300/134 ,  Y10T428/12549

Abstract: A thermal insulating ceramic layer for use on metal alloy components exposed to hostile thermal and chemical environment, such as a gas turbine. The thermal barrier coating may include cracks made by a series of steps, including subjecting at least a portion of the thermal barrier coating to a shockwave such that microcracks are formed in the thermal barrier coating without also substantially deforming the substrate.

Abstract translation: 用于暴露于恶劣的热和化学环境的金属合金组件的绝热陶瓷层，例如燃气轮机。 隔热涂层可以包括通过一系列步骤制成的裂纹，包括使至少一部分热障涂层受到冲击波，使得在热障涂层中形成微裂纹而不使基底基本上变形。

公开(公告)号：US20060246219A1

公开(公告)日：2006-11-02

申请号：US10558685

申请日：2004-02-25

Applicant: Yasuhiro Aoki ,  Akihiro Sato

Inventor： Yasuhiro Aoki ,  Akihiro Sato

IPC: B05D3/00

CPC classification number: C23C10/02 ,  F01D5/288 ,  F05C2201/0463 ,  F05D2300/132 ,  Y02T50/671 ,  Y10T428/12847 ,  Y10T428/12861 ,  Y10T428/1291 ,  Y10T428/12931 ,  Y10T428/12944

Abstract: A reaction control material that is Co, Cr or Ru, or an alloy having main component selected from a group consisting of Co, Cr, Ru is applied to the surface of an Ni-base superalloy before applying aluminum diffusion coating to the Ni-base superalloy. Thereby, it is possible to enhance the oxidation resistance of the Ni-base superalloy, and to control formation of a secondary reaction zone.

Abstract translation: 在将Ni扩散涂布施加到Ni基之前，将作为Co，Cr或Ru的反应控制材料或者选自Co，Cr，Ru的主成分的合金涂布在Ni基超耐热合金的表面上 超合金 由此，可以提高Ni基超合金的抗氧化性，并且可以控制二次反应区的形成。

公开(公告)号：US20050064213A1

公开(公告)日：2005-03-24

申请号：US10158305

申请日：2002-05-30

Applicant: Ramesh Subramanian ,  Brig Seth

Inventor： Ramesh Subramanian ,  Brig Seth

IPC: C23C4/18 ,  C23C14/08 ,  C23C14/58 ,  C23C16/40 ,  C23C16/56 ,  C23C28/00 ,  C23C28/04 ,  C23C30/00 ,  F01D5/28 ,  B32B9/00 ,  B32B15/04

CPC classification number: C23C14/5846 ,  C23C4/18 ,  C23C14/083 ,  C23C14/58 ,  C23C16/403 ,  C23C16/56 ,  C23C28/042 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/611 ,  Y02T50/67 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/24471 ,  Y10T428/26

Abstract: A device (10) is made, having a ceramic thermal barrier coating layer (16) characterized by a microstructure having gaps (18) with a sintering inhibiting material (22) disposed on the columns (20) within the gaps (18). The sintering resistant material (22) is stable over the range of operating temperatures of the device (10), is not soluble with the underlying ceramic layer (16) and is applied by a process that is not an electron beam physical vapor deposition process. The sintering inhibiting material (22) has a morphology adapted to improve the functionality of the sintering inhibiting material (22), characterized as continuous, nodule, rivulet, grain, crack, flake and combinations thereof and being disposed within at least some of the vertical and horizontal gaps.

Abstract translation: 制造具有陶瓷热障涂层（16）的装置（10），其特征在于具有间隙（18）的微结构，所述间隙具有设置在所述间隙（18）内的所述柱（20）上的烧结抑制材料（22）。 耐烧结材料（22）在器件（10）的操作温度的范围内是稳定的，不溶于下面的陶瓷层（16），并且通过不是电子束物理气相沉积工艺的工艺施加。 烧结抑制材料（22）具有适于改善烧结抑制材料（22）的功能的形态，其特征在于连续的，结节状，水滴状，晶粒状，裂纹，薄片状及其组合，并且设置在至少一些垂直 和水平间隙。

公开(公告)号：US20040237712A1

公开(公告)日：2004-12-02

申请号：US10482253

申请日：2004-05-24

Inventor： Iain Robert Whitaker ,  Richard Jameson Pavey

IPC: C22C029/00

CPC classification number: F16C33/121 ,  B22F2998/10 ,  C22C1/0433 ,  C22C32/0089 ,  F01D5/28 ,  F01D25/166 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/40 ,  F05D2240/50 ,  F05D2300/132 ,  F16C2360/24 ,  B22F1/0003 ,  B22F3/02 ,  B22F3/1007

Abstract: A sintered material and a method for the production thereof is described. The material comprises an alloy selected from one of the groups having a composition comprising in weight %: either Cr 5-30/Mo 0-15/Ni 0-25/W 0-15/C 0-5/Si 0-5/Fe 0-5/Mn 0-5/others 10max/Co balance, or Cr 10-20/Mo 0-15/Co 0-20/W 0-5/Fe 0-20/Al 0-5/Ti 0-5/others 15max/Ni balance; said alloy having incorporated therein from 3-15 weight % of Sn; and optionally from 1-6 weight % of a solid lubricant material.

Abstract translation: 对烧结材料及其制造方法进行说明。 该材料包括选自以下组中的一种的合金：具有重量％的组成：Cr 5-30 / Mo 0-15 / Ni 0-25 / W 0-15 / C 0-5 / Si 0-5 / Fe 0-5 / Mn 0-5 /其他10max / Co平衡，或Cr 10-20 / Mo 0-15 / Co 0-20 / W 0-5 / Fe 0-20 / Al 0-5 / Ti 0- 5 /其他15max / Ni平衡; 所述合金从其中加入3-15重量％的Sn; 和任选的1-6重量％的固体润滑剂材料。

公开(公告)号：US20030217792A1

公开(公告)日：2003-11-27

申请号：US10155257

申请日：2002-05-24

Applicant: Siemens Westinghouse Power Corporation

Inventor： Allister James

IPC: B32B015/01

CPC classification number: C22C19/03 ,  B22F5/04 ,  B22F7/08 ,  B22F2998/10 ,  B32B15/01 ,  C22C19/058 ,  F01D5/187 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/00 ,  F05D2230/21 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/131 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/607 ,  Y10T428/12944 ,  B22F3/15 ,  B22F2202/01

Abstract: A hybrid component (30) having a cast single crystal superalloy portion (32) and an attached powder metallurgy material portion (34). The component may be a blade (30) of a gas turbine engine having a single crystal airfoil section and a powder metallurgy material root section. The powder metallurgy material may extend to form a core (36) within the airfoil section and may include cooling passages 38. The single crystal portion has a relatively simple geometry so that casting yields are optimized. The powder metallurgical portion includes the lower stressed and more complicated geometry sections of the component. A method of forming such a component includes casting the single crystal superalloy portion, then using that portion to form part of the mold for forming the powder metallurgy material portion.

Abstract translation: 具有铸造单晶超合金部分（32）和附着的粉末冶金材料部分（34）的混合部件（30）。 该部件可以是具有单晶翼型部分和粉末冶金材料根部的燃气轮机的叶片（30）。 粉末冶金材料可以延伸以在翼型部分内形成芯部（36）并且可以包括冷却通道38.单晶部分具有相对简单的几何形状，使得铸造产量被优化。 粉末冶金部分包括部件的较低应力和更复杂的几何形状部分。 形成这种组分的方法包括浇铸单晶超合金部分，然后使用该部分形成用于形成粉末冶金材料部分的模具的一部分。

公开(公告)号：US06586118B2

公开(公告)日：2003-07-01

申请号：US09867489

申请日：2001-05-30

Applicant: Melvin Robert Jackson ,  Bernard Patrick Bewlay ,  Ji-Cheng Zhao

Inventor： Melvin Robert Jackson ,  Bernard Patrick Bewlay ,  Ji-Cheng Zhao

IPC: B32B1500

CPC classification number: F01D5/28 ,  B23K35/0222 ,  B23K35/28 ,  B23K35/30 ,  B23K35/32 ,  B23K35/322 ,  B23K35/325 ,  B32B15/01 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/121 ,  F05D2300/13 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/134 ,  F05D2300/142 ,  F05D2300/143 ,  F05D2300/222 ,  Y02T50/672 ,  Y10T428/12639 ,  Y10T428/12674 ,  Y10T428/12778 ,  Y10T428/12806 ,  Y10T428/12819 ,  Y10T428/12826 ,  Y10T428/12847 ,  Y10T428/12861 ,  Y10T428/12868 ,  Y10T428/12875 ,  Y10T428/12889

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece is a semi-solid braze that comprises a first component and a second component. The first component of the semi-solid braze comprises a first element and a second metallic element, wherein the first element is one of titanium, palladium, zirconium, niobium, germanium, silicon, and hafnium, and the second metallic element is a metal selected from the group consisting of titanium, palladium, zirconium, niobium, hafnium, aluminum, chromium, vanadium, platinum, gold, iron, nickel, and cobalt, the second metallic element being different from the first element. The second component has a melting temperature of at least about 1450° C. and comprises one of niobium, molybdenum, titanium, hafnium, silicon, boron, aluminum, tantalum, germanium, vanadium, tungsten, zirconium, and chromium. This abstract is submitted in compliance with 37 C.F.R. 1.72(b) with the understanding that it will not be used to interpret or limit the scope of or meaning of the claims.

Abstract translation: 一种具有至少约1500℃的熔融温度并且包括通过钎焊连接到第一部件的第一部件和第二部件的翼型件。 第一件包括第一铌基难熔金属金属间复合材料和第一种难熔金属金属间复合材料中的一种，第二件包括第二铌基难熔金属金属间复合物和第二种钼基难熔金属金属间化合物 综合。 将第一件连接到第二件的钎焊是包括第一部件和第二部件的半固体钎焊。 半固体钎焊的第一部件包括第一元件和第二金属元件，其中第一元件是钛，钯，锆，铌，锗，硅和铪之一，并且第二金属元素是选择的金属 从钛，钯，锆，铌，铪，铝，铬，钒，铂，金，铁，镍和钴组成的组中，第二金属元素不同于第一元素。 第二组分的熔融温度为至少约1450℃，并且包括铌，钼，钛，铪，硅，硼，铝，钽，锗，钒，钨，锆和铬中的一种。 本摘要根据37 C.F.R. 1.72（b），但有一项谅解，即不会用于解释或限制权利要求的范围或含义。