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。

公开(公告)号：US06575702B2

公开(公告)日：2003-06-10

申请号：US09682814

申请日：2001-10-22

Applicant: Melvin Robert Jackson ,  Aaron Todd Frost ,  Shyh-Chin Huang ,  Charles Gitah Mukira ,  Thomas Robert Raber ,  Raymond Alan White ,  Paul Leonard Dupree ,  Canan Uslu Hardwicke

Inventor： Melvin Robert Jackson ,  Aaron Todd Frost ,  Shyh-Chin Huang ,  Charles Gitah Mukira ,  Thomas Robert Raber ,  Raymond Alan White ,  Paul Leonard Dupree ,  Canan Uslu Hardwicke

IPC: F01D528

CPC classification number: B23P6/005 ,  B23P15/04 ,  F01D5/005 ,  F01D5/28 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/21 ,  F05D2230/23 ,  F05D2230/80 ,  F05D2300/11 ,  F05D2300/502 ,  F05D2300/606 ,  F05D2300/607 ,  Y02T50/67 ,  Y02T50/672 ,  Y10T29/49318 ,  Y10T29/49737

Abstract: Methods for repairing and manufacturing a gas turbine airfoil, and the airfoil repaired and manufactured with such methods are presented with, for example, the repair method comprising providing an airfoil having specified nominal dimensions, the airfoil comprising a first material, the first material having a creep life and a fatigue life, the airfoil further comprising a leading edge section and a trailing edge section; removing at least one portion of at least one section of the airfoil to create at least one deficit of material for the airfoil relative to the specified nominal dimensions, the at least one section selected from the group consisting of the leading edge section and the trailing edge section; providing at least one insert comprising a second material, the second material having a creep life that is at least substantially equal to the creep life of the first material, and a fatigue life that is at least substantially equal to the fatigue life of the first material; and disposing the at least one insert onto the airfoil such that the at least one deficit of material is substantially eliminated.

Abstract translation: 提供了用于修理和制造燃气涡轮机翼型的方法以及用这种方法修理和制造的翼型，例如，提供了修复方法，该修复方法包括提供具有特定标称尺寸的翼型件，该翼型件包括第一材料，第一材料具有 蠕变寿命和疲劳寿命，翼型件还包括前缘部分和后缘部分; 去除所述翼型件的至少一个部分的至少一部分以产生相对于所述特定公称尺寸的所述翼型件的至少一个缺口，所述至少一个部分选自由所述前缘部分和所述后缘 部分; 提供包括第二材料的至少一个插入件，所述第二材料具有至少基本上等于所述第一材料的蠕变寿命的蠕变寿命，以及至少基本等于所述第一材料的疲劳寿命的疲劳寿命 ; 以及将所述至少一个插入件设置在所述翼型件上，使得所述至少一个材料缺陷基本上被消除。

公开(公告)号：US20020124569A1

公开(公告)日：2002-09-12

申请号：US10044496

申请日：2002-01-10

Inventor： William D. Treece ,  Yungmo Kang Korean ,  Robert McKiernan

IPC: F02C007/10

CPC classification number: F02C3/05 ,  F02C7/08 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/231 ,  F05D2300/171 ,  F28D9/0018 ,  F28F2250/102

Abstract: A turbine engine includes a turbine driven by hot gas, a compressor rotating with the turbine to generate compressed air, an annular combustor coaxial with the turbine to combust fuel and compressed air to generate the hot gas, and an annular recuperator to recover heat from the turbine exhaust gas and heat the compressed air for combustion. The annular recuperator surrounds the turbine and includes two contiguous parts made from two materials having different thermal properties and joined to one another to form a single annular structure. One recuperator part is formed from a high-temperature material having a high thermal limit for exposure to high-temperature turbine exhaust gas, and the other recuperator part is formed from a material having a lower thermal limit than the high-temperature material for exposure to reduced-temperature turbine exhaust gas.

Abstract translation: 涡轮发动机包括由热气驱动的涡轮机，与涡轮机一起旋转以产生压缩空气的压缩机，与涡轮机同轴的环形燃烧器以燃烧燃料和压缩空气以产生热气体;以及环形换热器，用于从 涡轮机排气并加热压缩空气进行燃烧。 环形换热器围绕涡轮并且包括由具有不同热性质的两种材料制成的两个相邻部分并且彼此连接以形成单个环形结构。 一个换热器部分由具有高热限制的高温材料形成，用于暴露于高温涡轮机废气，另一个换热器部分由具有比用于暴露于高温涡轮机的高温材料的热限度低的材料形成 降低汽轮机废气排放。

公开(公告)号：US06431835B1

公开(公告)日：2002-08-13

申请号：US09690216

申请日：2000-10-17

Applicant: Michael Kolodziej ,  Bruce D. Wilson

Inventor： Michael Kolodziej ,  Bruce D. Wilson

IPC: F01D530

CPC classification number: F01D5/28 ,  F01D5/3092 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2250/71 ,  F05D2260/30 ,  F05D2300/611

Abstract: A compliant shim for use between the root of a gas turbine fan blade and a dovetail groove in a gas turbine rotor disk to reduce fretting therebetween. The compliant shim has first and second slots for engaging tabs extending from the fan blade root. The slots and tabs cooperate to hold the shim during engine operation. An oxidation layer covers the compliant shim.

Abstract translation: 用于在燃气轮机风扇叶片的根部和燃气涡轮机转子盘中的燕尾槽之间使用的柔性垫片以减少它们之间的微动。 顺应垫片具有第一和第二槽，用于接合从风扇叶片根延伸的突出部。 在发动机运行期间，槽和接头配合起来保持垫片。 氧化层覆盖柔顺垫片。

公开(公告)号：US06398499B1

公开(公告)日：2002-06-04

申请号：US09813626

申请日：2001-03-19

Applicant: Joseph Simonetti ,  Bruce Wilson

Inventor： Joseph Simonetti ,  Bruce Wilson

IPC: F01D522

CPC classification number: F01D5/28 ,  F01D5/3092 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2250/71 ,  F05D2260/30 ,  F05D2300/611

Abstract: A compliant shim for use between the root of a gas turbine fan blade and a dovetail groove in a gas turbine rotor disk to reduce fretting therebetween. The compliant shim has first and second slots for engaging tabs extending from the fan blade root. The slots and tabs cooperate to hold the shim during engine operation. An oxidation layer covers the compliant shim. The shim is augmented with an upstanding wall and a seal element to seal the gap that exists between platform edges of adjacent fan blades. This simple combination solves two complex problems, fatigue of fan assembly parts and loss of operating efficiency caused by fluid flow leakage.

公开(公告)号：US09303522B2

公开(公告)日：2016-04-05

申请号：US12308523

申请日：2007-06-14

Applicant: Manfred A. Daeubler ,  Horst Mueller-Wittek ,  Renate Mendritzki ,  André Werner ,  Heinrich Walter

Inventor： Manfred A. Daeubler ,  André Werner ,  Heinrich Walter

IPC: B05D3/00 ,  B32B43/00 ,  F01D11/12 ,  B23P6/00 ,  C23C10/16 ,  C23C10/18 ,  C23C26/00

CPC classification number: F01D11/12 ,  B23P6/007 ,  C23C10/16 ,  C23C10/18 ,  C23C26/00 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/762 ,  F05D2230/10 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/40 ,  F05D2230/80 ,  F05D2300/11 ,  F05D2300/224 ,  F05D2300/228

Abstract: A method for repairing run-in coatings is provided. The method includes the steps of filling a damaged site of the run-in coating with a filling material having a material composition that corresponds to a material composition of the run-in coating or is comparable to the material composition of the run-in coating or having material properties that are comparable to material properties of the run-in coating; drying the filling material that has been filled into the damaged site; depositing a donor diffusion layer over an area of the damaged site and onto the dried filling material; and thermally treating the run-in coating at least in the area of the damaged site to locally diffuse at least one metallic element from the donor diffusion layer into the filling material.

Abstract translation: 提供了修补磨损涂层的方法。 该方法包括以下填充材料的填充材料的填充材料的填充损伤部位的步骤：材料组成与导入涂层的材料组成相对应，或者可以与渗入涂层的材料组成相当 具有与外加涂层的材料性能相当的材料性质; 干燥已填充到损坏场所的填充材料; 在受损部位的区域上沉积供体扩散层，并将其施加到干燥的填充材料上; 以及至少在受损部位的区域热处理所述接合涂层，以将至少一种金属元素从所述供体扩散层局部扩散到所述填充材料中。

公开(公告)号：US20110299996A1

公开(公告)日：2011-12-08

申请号：US13202260

申请日：2010-01-30

Applicant: Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling

Inventor： Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling

IPC: F01D5/14 ,  C23F13/06 ,  B05D1/18 ,  C23C4/12 ,  B05D5/00 ,  B05D1/02 ,  C23F13/00 ,  C23C16/44

CPC classification number: F01D9/04 ,  C23C28/321 ,  C23C28/322 ,  C23C28/34 ,  C23C28/341 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/36 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/314 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/134 ,  F05D2300/161 ,  F05D2300/21 ,  F05D2300/222 ,  F05D2300/226 ,  F05D2300/228 ,  F05D2300/48 ,  Y02T50/67 ,  Y02T50/6765

Abstract: A gas turbine component and a method for producing an anti-erosion coating system are disclosed. The gas turbine component includes a basic material, on which an anti-erosion coating system is provided that is a multilayer system including at least one ductile metal layer and at least one hard, ceramics-containing layer for forming a partial anti-erosion system. At least one anti-corrosion layer that has a lower electrochemical potential than the basic material is provided between the partial anti-erosion system and the basic material, thus providing cathodic corrosion protection.

Abstract translation: 公开了一种燃气轮机部件及其制造方法。 燃气轮机部件包括基材，其上设置有防腐蚀涂层系统，其是包括至少一个延性金属层和至少一个用于形成部分抗侵蚀系统的含硬陶瓷的层的多层系统。 在部分抗侵蚀系统和基础材料之间提供至少一个具有比基本材料更低的电化学电位的防腐蚀层，从而提供阴极腐蚀保护。