公开(公告)号：US06756082B1

公开(公告)日：2004-06-29

申请号：US09640073

申请日：2000-08-17

Applicant: Ramesh Subramanian ,  Brij B. Seth

Inventor： Ramesh Subramanian ,  Brij B. Seth

IPC: B05D136

CPC classification number: C23C14/5846 ,  C23C14/083 ,  C23C14/58 ,  C23C16/403 ,  C23C16/56 ,  C23C28/00 ,  C23C28/04 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/611 ,  Y02T50/67

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.

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。

公开(公告)号：US06709771B2

公开(公告)日：2004-03-23

申请号：US10155257

申请日：2002-05-24

Applicant: James Allister

Inventor： James Allister

IPC: B22F704

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：US20040022646A1

公开(公告)日：2004-02-05

申请号：US10343447

申请日：2003-01-31

Inventor： Reinhard Garczorz ,  Fritz-Martin Scholz

IPC: F04B039/06

CPC classification number: C22C1/0416 ,  F04C18/123 ,  F04C2240/10 ,  F04C2240/20 ,  F05C2201/0436 ,  F05C2201/0442 ,  F05C2201/0466 ,  F05C2201/903 ,  F05C2203/0817 ,  F05C2251/046

Abstract: The compressor has two rotors (14, 16), which are rotatably mounted in a housing (10) by means of a shaft each, the rotors (14, 16) rotating without contact with the housing. The rotors (14, 16) consist of a powder-metallurgical AlnullSi alloy, and the housing (10) consists essentially of aluminum.

Abstract translation: 压缩机具有两个转子（14,16），它们通过轴可旋转地安装在壳体（10）中，转子（14,16）旋转而不与壳体接触。 转子（14,16）由粉末冶金Al-Si合金组成，壳体（10）基本上由铝组成。

公开(公告)号：US06598781B2

公开(公告)日：2003-07-29

申请号：US10176782

申请日：2002-06-24

Applicant: Wayne Charles Hasz ,  Robert Alan Johnson ,  Ching-Pang Lee ,  Mark Gerard Rettig ,  Nesim Abuaf ,  John Howard Starkweather

Inventor： Wayne Charles Hasz ,  Robert Alan Johnson ,  Ching-Pang Lee ,  Mark Gerard Rettig ,  Nesim Abuaf ,  John Howard Starkweather

IPC: C23C2602

CPC classification number: F01D5/187 ,  B22F2998/00 ,  B23K35/0233 ,  B23K35/0244 ,  B23K35/025 ,  B23K35/3006 ,  B23K35/3033 ,  B23K35/3046 ,  B23K35/3053 ,  B23K35/322 ,  B23K37/047 ,  B23K2101/001 ,  B32B15/01 ,  C21D9/08 ,  C23C24/10 ,  C23C26/02 ,  F01D5/08 ,  F01D25/12 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/237 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/611 ,  F23R2900/03045 ,  F28F13/12 ,  F28F13/185 ,  F28F21/087 ,  Y10T29/49337 ,  Y10T29/49393 ,  Y10T428/12014 ,  Y10T428/12063 ,  Y10T428/12097 ,  Y10T428/12104 ,  Y10T428/12389 ,  Y10T428/12431 ,  Y10T428/12486 ,  Y10T428/12931 ,  Y10T428/12993 ,  B22F3/22 ,  B22F5/04

Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.

公开(公告)号：US06547522B2

公开(公告)日：2003-04-15

申请号：US09681851

申请日：2001-06-18

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

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

IPC: F01D1112

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.

公开(公告)号：US20030062256A1

公开(公告)日：2003-04-03

申请号：US10237696

申请日：2002-09-10

Applicant: SNECMA MOTEURS

Inventor： Gerard Gueldry ,  Claude Mons

IPC: C23C014/32 ,  C23C014/00 ,  F16J015/56 ,  H05H001/24 ,  B23K013/01

CPC classification number: F01D11/02 ,  F01D11/001 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/10 ,  F05D2300/21 ,  F05D2300/502 ,  Y02T50/67 ,  Y02T50/671

Abstract: In order to make labyrinth seal lips on the periphery of a metal moving part of a turbomachine, a thick layer of refractory material that adheres to the metal is made prior to assembling the moving part, the refractory material advantageously comprising at least one metal selected for example from Fe, Co, and Ni, together with at least one ceramic selected for example from borides, nitrides, carbides, and refractory oxides. The labyrinth seal lips that are to be made are machined to their final dimensions in the deposited thick layer.

Abstract translation: 为了在涡轮机的金属运动部分的周边上制造迷宫式密封唇，在组装移动部件之前制成粘附于金属的厚层耐火材料，耐火材料有利地包括至少一种选自 例如Fe，Co和Ni，以及选自例如硼化物，氮化物，碳化物和难熔氧化物中的至少一种陶瓷。 要制成的迷宫式密封唇被加工成沉积的厚层中的最终尺寸。

公开(公告)号：US20020168537A1

公开(公告)日：2002-11-14

申请号：US10176782

申请日：2002-06-24

Inventor： Wayne Charles Hasz ,  Robert Alan Johnson ,  Ching-Pang Lee ,  Mark Gerard Rettig ,  Nesim Abuaf ,  John Howard Starkweather

IPC: B32B015/16 ,  B23K031/02 ,  B22F007/04 ,  B22F005/00

CPC classification number: F01D5/187 ,  B22F2998/00 ,  B23K35/0233 ,  B23K35/0244 ,  B23K35/025 ,  B23K35/3006 ,  B23K35/3033 ,  B23K35/3046 ,  B23K35/3053 ,  B23K35/322 ,  B23K37/047 ,  B23K2101/001 ,  B32B15/01 ,  C21D9/08 ,  C23C24/10 ,  C23C26/02 ,  F01D5/08 ,  F01D25/12 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/237 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/611 ,  F23R2900/03045 ,  F28F13/12 ,  F28F13/185 ,  F28F21/087 ,  Y10T29/49337 ,  Y10T29/49393 ,  Y10T428/12014 ,  Y10T428/12063 ,  Y10T428/12097 ,  Y10T428/12104 ,  Y10T428/12389 ,  Y10T428/12431 ,  Y10T428/12486 ,  Y10T428/12931 ,  Y10T428/12993 ,  B22F3/22 ,  B22F5/04

Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.

公开(公告)号：US06422010B1

公开(公告)日：2002-07-23

申请号：US09879371

申请日：2001-06-11

Applicant: Gerald J. Julien

Inventor： Gerald J. Julien

IPC: F01B2910

CPC classification number: F01D25/005 ,  F05C2201/0466 ,  F05D2230/13 ,  F05D2230/21 ,  F05D2230/26 ,  F05D2230/41 ,  F05D2300/133 ,  F05D2300/505 ,  F05D2300/506 ,  Y02T50/671

Abstract: The invention includes processes and products made by the processes. The processes include making forms and parts by friable mold casting or die casting using molten Nitinol poured or injected into the mold or die. After the Nitinol has cooled to a solid state, it is removed from the mold by disintegrating the friable material of the mold and is heated to an elevated temperature under high pressure to consolidate the Nitinol and remove any internal voids. The parts and forms are then heat treated to reduce brittleness and improve toughness and impact strength. The part may be hot machined to reduce it to near net size, and may be ground to reduce the part to the exact specified part size. For example, cylindrical parts can be centerless ground; balls can be ground in a conventional ball grinder; flat stock can be surface ground. For parts requiring a smooth surface finish, polishing or lapping provides the specified surface finish on the part, down to 0.5 microinch RMS or finer. The part may be heat treated to obtain the desired hardness, from RC40 to RC65. An integral surface oxide of any of several colors can be formed on the surface of the part. The oxide surface may itself be polished to an even finer surface finish. Shape memory effect may be obtained in Type 60 Nitinol parts and forms that have been hot-worked by heat treating to about 675° C.-700° C. and oven cooling slowly over 8-10 hours to ambient temperature.

Abstract translation: 本发明包括由该方法制备的方法和产品。 这些方法包括通过使用熔融的镍钛诺（Eloy）浇注或注入模具或模具中的脆性模铸或压铸来制造形式和零件。 在镍钛诺已经冷却到固态之后，通过将模具的易碎材料分解，将其从模具中除去，并在高压下加热至高温以固化镍钛诺并除去任何内部空隙。 然后对这些部件和形式进行热处理以降低脆性并提高韧性和冲击强度。 该部件可以被热加工以将其减小到接近净尺寸，并且可以被研磨以将部件减小到确切的指定部件尺寸。 例如，圆柱形部件可以是无心磨削的; 球可以在传统的球磨机中研磨; 平面库存可以是地面。 对于需要光滑表面光洁度的部件，抛光或研磨可在部件上提供指定的表面光洁度，低至0.5微英寸RMS或更细。 该部件可以被热处理以获得期望的硬度，从RC40到RC65。 可以在部件的表面上形成多种颜色中的任何一种的整体表面氧化物。 氧化物表面本身可以被抛光到更细的表面光洁度。 形状记忆效应可以通过热处理至约675℃-700℃和烘箱在8-10小时内缓慢冷却至环境温度的60型镍钛诺部件和形式中获得。

公开(公告)号：US06419453B2

公开(公告)日：2002-07-16

申请号：US09797989

申请日：2001-03-05

Applicant: Yutaka Fukui ,  Hiroyuki Doi ,  Masahiko Arai ,  Ryo Hiraga ,  Kenichiro Nomura ,  Toshio Fujita ,  Yasuhiko Tanaka

Inventor： Yutaka Fukui ,  Hiroyuki Doi ,  Masahiko Arai ,  Ryo Hiraga ,  Kenichiro Nomura ,  Toshio Fujita ,  Yasuhiko Tanaka

IPC: B63H126

CPC classification number: F01D5/28 ,  C21D8/0205 ,  C21D9/28 ,  C21D9/38 ,  C22C38/001 ,  C22C38/44 ,  C22C38/46 ,  C22C38/48 ,  C22C38/52 ,  C22C38/54 ,  F01D25/005 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/31 ,  F05D2240/60 ,  F05D2300/131 ,  F05D2300/132

Abstract: The main object of the present invention is to provide a steam turbine rotor shaft whose high-temperature strength is excellent at a selected temperature of 650 degrees C. A steam turbine rotor shaft comprising 0.05% to 0.20% by weight of carbon, 0.20% or less by weight of silicon, 0.05% to 1.5% by weight of manganese, 0.01% to 1.0% by weight of nickel, 9.0% to 13.0% by weight of chrome, 0.05% to 2.0% by weight of molybdenum, 0.5% to 5.0% by weight of tungsten, 0.05% to 0.30% by weight of vanadium, 0.01% to 0.20% by weight of niobium, 0.5% to 10.0% by weight of cobalt, 0.01% to 0.1% by weight of nitrogen, 0.001% to 0.030% by weight of boron, 0.0005% to 0.006% by weight of aluminum, and the remaining parts substantially comprising iron and inevitable impurities.

Abstract translation: 本发明的主要目的在于提供一种蒸汽轮机转子轴，其特征在于，在选定温度为650度的汽轮机转子轴的选定温度下，包括0.05重量％至0.20重量％的碳，0.20重量％以下，通过 重量的硅，0.05〜1.5％的锰，0.01〜1.0％的镍，9.0〜13.0％的铬，0.05〜2.0％的钼，0.5〜5.0％的 重量的钨，0.05〜0.30％的钒，0.01〜0.20％的铌，0.5〜10.0％的钴，0.01〜0.1％的氮，0.001〜0.030％的 重量的硼，0.0005％至0.006％的铝，其余部分基本上包含铁和不可避免的杂质。

公开(公告)号：US06296945B1

公开(公告)日：2001-10-02

申请号：US09393415

申请日：1999-09-10

Applicant: Ramesh Subramanian

Inventor： Ramesh Subramanian

IPC: B32B900

CPC classification number: C23C14/5846 ,  C23C14/083 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/611 ,  Y02E20/16 ,  Y10S428/937

Abstract: A turbine component (10), such as a turbine blade, is provided which is made of a metal alloy (22) and a base columnar thermal barrier coating (20) on the alloy surface, where a heat resistant ceramic oxide sheath material (32′ or 34′) covers the columns (28), and the sheath material is the reaction product of a precursor ceramic oxide sheath material and the base thermal barrier coating material.

Abstract translation: 提供涡轮机部件（10），例如涡轮叶片，其由合金表面上的金属合金（22）和基体柱状热障涂层（20）制成，其中耐热陶瓷氧化物护套材料（32 '或34'）覆盖柱（28），护套材料是前体陶瓷氧化物护套材料与基底热障涂层材料的反应产物。