公开(公告)号：US20040109786A1

公开(公告)日：2004-06-10

申请号：US10314083

申请日：2002-12-06

Inventor： Kevin Swayne O'Hara ,  William Scott Walston ,  Charles Gitahi Mukira ,  Melvin Robert Jackson

IPC: C22C019/05

CPC classification number: F01D5/28 ,  C22C19/056 ,  F05C2201/0466 ,  F05D2300/607

Abstract: A composition of matter is about 1 to about 3 percent rhenium, from about 6 to about 9 percent aluminum, from 0 to about 0.5 percent titanium, from about 4 to about 6 percent tantalum, from about 12.5 to about 15 percent chromium, from about 3 to about 10 percent cobalt, from about 2 to about 5 percent tungsten, from 0 to about 0.2 percent hafnium, from 0 to about 1 percent silicon, from 0 to about 0.25 percent molybdenum, from 0 to about 0.25 percent niobium, balance nickel and minor elements. The composition is preferably made into a substantially single crystal article, such as a component of a gas turbine engine.

Abstract translation: 物质的组成为约1至约3％的铼，约6至约9％的铝，0至约0.5％的钛，约4至约6％的钽，约12.5至约15％的铬，来自约 3至约10％的钴，约2至约5％的钨，0至约0.2％的铪，0至约1％的硅，0至约0.25％的钼，0至约0.25％的铌，余量为 和次要元素。 组合物优选制成基本上单晶的制品，例如燃气涡轮发动机的部件。

公开(公告)号：US20040001965A1

公开(公告)日：2004-01-01

申请号：US10064273

申请日：2002-06-27

Applicant: General Electric Company One Reserach Circle

Inventor： Ji-Cheng Zhao ,  Don Mark Lipkin

IPC: B32B015/00 ,  B05D001/36 ,  C23C014/28

CPC classification number: F01D5/28 ,  C23C4/073 ,  C23C26/00 ,  C23C28/023 ,  C23C28/028 ,  F05C2201/0466 ,  F05D2300/121 ,  Y02T50/67 ,  Y10T428/12458 ,  Y10T428/12493 ,  Y10T428/12736 ,  Y10T428/1275 ,  Y10T428/12771 ,  Y10T428/12944 ,  Y10T428/263 ,  Y10T428/265

Abstract: A coated article, a coating for protecting an article, and a method for protecting an article are provided. The article comprises a metallic substrate and a substantially single-phase coating disposed on the substrate, wherein the coating comprises nickel (Ni) and at least about 30 atomic percent aluminum (Al); the coating further comprises a gradient in Al composition, the gradient extending from a first Al concentration level at an outer surface of the coating to a second Al concentration level at an interface between the substantially single-phase coating and the substrate, wherein the first Al concentration level is greater than the second Al concentration level and the second concentration level is at least about 30 atomic percent Al.

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：US20030088979A1

公开(公告)日：2003-05-15

申请号：US10288004

申请日：2002-11-04

Applicant: Kabushiki Kaisha Toyota Jidoshokki

Inventor： Masanobu Tomita ,  Hironobu Tsushima

IPC: B23P015/00

CPC classification number: F04B27/0886 ,  B21K1/02 ,  B21K3/00 ,  B23P15/00 ,  F05C2201/021 ,  F05C2201/0466 ,  F05C2253/12 ,  Y10T29/49236

Abstract: A method of producing an aluminum ball, comprising the steps of: a cutting step of cutting a bar-shaped blank formed of a material containing aluminum as a major component, into cut pieces; an aluminum-ball forming step of forming each of the cut pieces into the aluminum ball by semi-closed die forging, said aluminum ball having a flash formed on an outer circumferential surface thereof; and a flash removing step of removing the flash from the aluminum ball formed by forging. Also disclosed is a method of producing a shoe for a compressor, from the aluminum ball.

Abstract translation: 一种制造铝球的方法，包括以下步骤：将由含有铝作为主要成分的材料形成的棒状坯料切割成切割步骤; 铝球形成步骤，通过半封闭模锻将每个切割片形成为铝球，所述铝球在其外圆周表面上形成闪光; 以及从通过锻造形成的铝球除去闪光的闪光除去步骤。 还公开了一种从铝球制造用于压缩机的鞋的方法。

公开(公告)号：US20020192074A1

公开(公告)日：2002-12-19

申请号：US09681851

申请日：2001-06-18

Inventor： Norman Arnold Turnquist ,  Mahmut Faruk Aksit ,  Farshad Ghasripoor ,  Raymond Edward Chupp

IPC: F01D011/12

CPC classification number: F01D11/122 ,  F05C2201/0466 ,  F05D2240/56 ,  F05D2260/30 ,  F05D2300/224 ,  F05D2300/43 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/614 ,  F05D2300/702 ,  F16J15/3288 ,  F16J15/445

Abstract: The present invention provides, in one embodiment, an annular turbine seal for disposition in a turbine between a rotatable component having an axis of rotation and a turbine housing about the same axis of rotation. The turbine seal has a plurality of arcuate seal carrier segments that have an abradable portion secured to the seal carrier segments. In addition, at least one spring is disposed on the seal carrier segment to exert a force and maintain the seal carrier segment adjacent to the rotatable component.

Abstract translation: 在一个实施例中，本发明提供了一种环形涡轮密封件，用于在具有旋转轴线的可旋转部件和围绕相同旋转轴线的涡轮机壳体之间配置在涡轮机中。 涡轮密封件具有多个弓形密封载体段，其具有固定到密封载体段的可磨损部分。 此外，至少一个弹簧设置在密封件承载部分上以施加力并将密封载体部分保持在可旋转部件附近。

公开(公告)号：US06492034B1

公开(公告)日：2002-12-10

申请号：US09190364

申请日：1998-11-12

Applicant: Mohamed Nazmy ,  Martin Scheu ,  Markus Staubli

Inventor： Mohamed Nazmy ,  Martin Scheu ,  Markus Staubli

IPC: B32B502

CPC classification number: F01D25/08 ,  F05C2201/0466 ,  F05D2300/2118 ,  F05D2300/614 ,  F23R3/007 ,  Y10T428/12153 ,  Y10T428/12444 ,  Y10T428/12479 ,  Y10T428/12535 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12944 ,  Y10T428/12951 ,  Y10T428/131

Abstract: In a heat shield (1), in particular for combustion chambers and for thermal fluid flow machines, the heat shield consists of a feltlike material (3) composed of compressed and sintered intermetallic fibers. Advantageously, the intermetallic fibers consist of an iron based or nickel based intermetallic phase.

Abstract translation: 在隔热罩（1）中，特别是用于燃烧室和用于热流体流动机器的隔热罩（1）由隔热材料（3）组成，该材料由压缩和烧结的金属间纤维构成。 有利地，金属间纤维由铁基或镍基金属间相组成。

公开(公告)号：US20020131884A1

公开(公告)日：2002-09-19

申请号：US10001018

申请日：2001-11-02

Inventor： Masaru Mito ,  Masashi Yoshimura ,  Masaaki Takahashi

IPC: F04C018/16

CPC classification number: F04C29/005 ,  F04C2/086 ,  F04C2/18 ,  F04C13/002 ,  F04C15/0038 ,  F04C15/0088 ,  F04C15/0096 ,  F04C18/084 ,  F04C18/16 ,  F04C2220/12 ,  F05C2201/0442 ,  F05C2201/0466 ,  F05C2203/0808

Abstract: In a dry vacuum pump including: a casing having an inner cylinder (1a) communicating with an inlet (6) and an outlet (7) of the pump; shafts (15b) supported by the casing; spiral toothlike parts (15a) formed on the shaft (15b); a plurality of screw rotors (15), each of which includes the shaft (15b) and the spiral toothlike parts (15a) received in the inner cylinder (1a) intermeshing with each other; timing gears (16, 19), each of which is attached to the respective shafts (15b) of the screw rotors (15) and intermeshes with each other; and locking mechanisms (17), each of which for fixing the timing gear (16, 19) to the shaft (15b), both of the shaft (15b) and the toothlike part (15a) made of spheroidal graphite cast iron containing 20 to 30 wt % of nickel are casted integrally. With the construction described above, a problem such that a degree of vacuum deteriorates due to peeling of a resin coating is solved as to a dry vacuum pump pumping corrosive gas. A tapered face of 1/(20L) is formed with respect to the toothlike part (15a) so that an outer diameter of the toothlike part (15a) is shortened from the center of the toothlike part (15a) to the outlet side of the fluid, L being a length of the toothlike part, and a aground finish-surface is formed with respect to the toothlike part (15a) so that a diameter of the toothlike part (15a) is shortened by 3/100 to 4/100 mm from a position, where is about 10 mm offset toward the inlet side from the center of the toothlike part (15a), to the outlet side. With this construction, a seizure of the toothlike part (15a) is prevented from occurring. Nitrogen gas is supplied into the casing and an outlet path (20) connecting the outlet (7) with a scrubber (11) is a straight pipe, in which a silencer is removed. With this construction, heat capacity of the gas discharged from the outlet (7) is increased and reaction products are prevented from depositing in the outlet path (20).

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。