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1.发明授权Structure and method for forming detailed channels for thin walled components using thermal spraying 有权使用热喷涂形成薄壁部件的详细通道的结构和方法公开(公告)号：US08815371B2
公开(公告)日：2014-08-26
申请号：US12420135
申请日：2009-04-08
IPC分类号： B32B3/00 , B32B3/20 , F01D5/08 , F01D5/20 , F01D5/28 , C23C4/18 , B23P15/00 , C23C4/08 , F01D5/18 , B23P15/04 , F01D25/12 , C23C4/06 , F02C7/12
CPC分类号： F01D5/18 , B23P15/00 , B23P15/04 , B23P2700/06 , B23P2700/13 , C23C4/06 , C23C4/073 , C23C4/185 , F01D5/288 , F01D25/12 , F02C7/12 , F05D2230/90 , F05D2300/21 , Y10T428/24612 , Y10T428/24744
摘要： A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel.
摘要翻译： 具有地下冷却通道的涂覆的基底，其没有靠近基底和涂层之间的接缝设置角部。 一种用于形成这种结构的方法，包括在基板的表面中形成凹槽，形成具有配合部分的预成型件和突出部分，将预成型件的配合部分插入凹槽中，使预成型件的突出部分突出 超过基板的表面，将涂层材料层施加到基板的表面和执行的突出部分，并且移除预成型件，从而形成冷却通道。
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公开(公告)号：US07905016B2
公开(公告)日：2011-03-15
申请号：US11784986
申请日：2007-04-10
IPC分类号： B23P15/02
CPC分类号： B23P15/04 , B22F3/1146 , B22F5/04 , B22F7/006 , B22F2003/242 , B22F2003/244 , B22F2003/248 , B22F2998/10 , F01D5/147 , F01D25/12 , F05D2230/31 , F05D2230/90 , F05D2260/20 , F05D2260/203 , F05D2300/611 , Y10T29/49336 , Y10T29/49337 , B22F3/1125 , B22F3/15 , B22F3/24
摘要： A turbine airfoil system for forming a turbine airfoil that is usable in a turbine engine. The airfoil may be formed from a porous material shaped into an outer airfoil shape. The porous material may include an inner central spar capable of supporting the turbine airfoil an outer porous region and an outer coating. The porous material facilitates efficient cooling of the turbine airfoil.
摘要翻译： 一种用于形成可用于涡轮发动机的涡轮机翼型的涡轮机翼型系统。 翼型件可以由成形为外翼型的多孔材料形成。 多孔材料可以包括能够支撑涡轮机翼面外部多孔区域和外部涂层的内部中心翼梁。 多孔材料有助于涡轮机翼型的有效冷却。
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公开(公告)号：US20100028163A1
公开(公告)日：2010-02-04
申请号：US12183185
申请日：2008-07-31
CPC分类号： C22C19/03 , C22C19/07 , Y10T29/4932 , Y10T428/12014 , Y10T428/12063
摘要： An intermediate component includes a first wall member, a leachable material layer, and a precursor wall member. The first wall member has an outer surface and first connecting structure. The leachable material layer is provided on the first wall member outer surface. The precursor wall member is formed adjacent to the leachable material layer from a metal powder mixed with a binder material, and includes second connecting structure.
摘要翻译： 中间组分包括第一壁构件，可浸出材料层和前体壁构件。 第一壁构件具有外表面和第一连接结构。 可浸出材料层设置在第一壁构件外表面上。 前体壁构件由与粘合剂材料混合的金属粉末相邻于可浸出材料层形成，并且包括第二连接结构。
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4.发明申请Corrosion Resistant Alloy Compositions with Enhanced Castability and Mechanical Properties 审中-公开具有增强铸造性和机械性能的耐腐蚀合金组合物公开(公告)号：US20090041615A1
公开(公告)日：2009-02-12
申请号：US12173983
申请日：2008-07-16
IPC分类号： C22C19/05
CPC分类号： C22C19/056 , C22C19/057 , C22C30/00
摘要： Disclosed are novel nickel-base alloy compositions that may be cast as a single crystal or directionally solidified alloy consisting essentially of, by weight: 8-12% Cr, 10-14% Co, 0.3-0.9% Mo, 3-7% W, 2-8% Ta, 2.0-5.5% Al, 1.5-5.0% Ti, up to 2% Nb, less than 0.1% B, less than 0.1% Zr, 0.05-0.15% C, less than 0.5% Hf, 2-4% Re, 0.05-0.2% Si, up to 0.015% S, up to 0.1% La, up to 0.1% Y, up to 0.1% Ce, up to 0.1% Nd, up to 0.1% Dy, up to 0.1% Pr, up to 0.1% Gd, balance is Ni, and wherein (La+Y+Ce+Nd+Dy+Pr+Gd) is 0.001-0.1%. The compositions for the nickel-base superalloy have a balance between oxidation resistance, corrosion resistance, castability, and mechanical properties, such as creep resistance and thermo-mechanical fatigue resistance.
摘要翻译： 公开了可以铸造为单晶或定向凝固合金的新型镍基合金组合物，其基本上由以重量计：8-12％Cr，10-14％Co，0.3-0.9％Mo，3-7％W ，2-8％Ta，2.0-5.5％Al，1.5-5.0％Ti，至多2％Nb，小于0.1％B，小于0.1％Zr，0.05-0.15％C，小于0.5％Hf，2 -4％Re，0.05-0.2％Si，至多0.015％S，至多0.1％La，至多0.1％Y，至多0.1％Ce，至多0.1％Nd，至多0.1％Dy，至多0.1 ％Pr，高达0.1％的Gd，余量为Ni，其中（La + Y + Ce + Nd + Dy + Pr + Gd）为0.001-0.1％。 镍基超级合金的组合物在抗氧化性，耐腐蚀性，浇铸性和机械性能如抗蠕变性和耐热机械疲劳性之间具有平衡。
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公开(公告)号：US20080253923A1
公开(公告)日：2008-10-16
申请号：US11784987
申请日：2007-04-10
IPC分类号： C22C19/05
CPC分类号： C22C19/05
摘要： A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is suited for components of gas or steam turbine engines including blades and vanes.
摘要翻译： 公开了一种在氧化环境中形成氧化铬垢的镍基超级合金。 该合金在干燥或潮湿的气氛中在低于900℃的温度下提供良好的抗氧化性。 超级合金适用于包括叶片和叶片的气体或汽轮机发动机的部件。
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公开(公告)号：US20080253894A1
公开(公告)日：2008-10-16
申请号：US11784988
申请日：2007-04-10
CPC分类号： B23P15/006 , B21J1/00 , B21K1/32 , B21K3/00 , F01D5/02 , Y10T29/4932 , Y10T29/49321
摘要： A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an outer ring formed from a first steel material, and a disk formed from a second material, such as a low alloy steel, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged.
摘要翻译： 一种形成用于涡轮发动机的转子的方法，使得转子由两种材料形成，包括：由第一钢材形成的外圈和由诸如低合金钢的第二材料形成的盘，其具有较大的 热膨胀系数比形成内盘的第一种材料高。 环可以包括具有圆锥形状的内孔，并且盘可以具有圆锥形的外表面和具有大于环的一部分的部分的直径。 可以加热环，使得孔扩大到比内盘最大直径大的尺寸。 环可以定位在盘上并允许冷却以允许环附接到盘。 然后可以共同锻造环和盘。
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公开(公告)号：US08096751B2
公开(公告)日：2012-01-17
申请号：US12183168
申请日：2008-07-31
IPC分类号： F01D5/14
CPC分类号： F01D5/3061
摘要： A component for use in a turbine engine including a first member and a second member associated with the first member. The second member includes a plurality of connecting elements extending therefrom. The connecting elements include securing portions at ends thereof that are received in corresponding cavities formed in the first member to attach the second member to the first member. The connecting elements are constructed to space apart a first surface of the second member from a first surface of the first member such that at least one cooling passage is formed between adjacent connecting elements and the first surface of the second member and the first surface of the first member.
摘要翻译： 一种用于涡轮发动机的部件，包括第一构件和与第一构件相关联的第二构件。 第二构件包括从其延伸的多个连接元件。 连接元件包括在其端部处的固定部分，其接收在形成在第一构件中的相应空腔中，以将第二构件附接到第一构件。 连接元件被构造成使第二构件的第一表面与第一构件的第一表面分开，使得在相邻的连接元件和第二构件的第一表面之间形成至少一个冷却通道， 第一名成员
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8.发明授权Combustion turbine component having rare earth NiCrAl coating and associated methods 有权具有稀土NiCrAl涂层的燃烧涡轮机组件及相关方法公开(公告)号：US08043718B2
公开(公告)日：2011-10-25
申请号：US12194582
申请日：2008-08-20
CPC分类号： C23C28/347 , B22F1/0018 , B22F7/04 , B22F2998/10 , C22C19/058 , C22C32/0026 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , Y10T428/12028 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , B22F9/082 , B22F9/04 , B22F3/115
摘要： A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes nickel (Ni), chromium (Cr), aluminum (Al), and yttrium (Y). Furthermore, the alloy coating includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). The alloy coating also includes at least one rare earth element, and an oxide of at least one of the yttrium (Y) and the at least one rare earth element.
摘要翻译： 燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。 合金涂层（14）包括镍（Ni），铬（Cr），铝（Al）和钇（Y）。 此外，合金涂层包括钛（Ti），钽（Ta），钨（W）和铼（Re）中的至少一种。 合金涂层还包括至少一种稀土元素和至少一种钇（Y）和至少一种稀土元素的氧化物。
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9.发明申请Combustion Turbine Component Having Rare Earth NiCrAl Coating and Associated Methods 有权具有稀土NiCrAl涂层的燃烧涡轮机组件及相关方法公开(公告)号：US20090075111A1
公开(公告)日：2009-03-19
申请号：US12194582
申请日：2008-08-20
CPC分类号： C23C28/347 , B22F1/0018 , B22F7/04 , B22F2998/10 , C22C19/058 , C22C32/0026 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , Y10T428/12028 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , B22F9/082 , B22F9/04 , B22F3/115
摘要： A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes nickel (Ni), chromium (Cr), aluminum (Al), and yttrium (Y). Furthermore, the alloy coating includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). The alloy coating also includes at least one rare earth element, and an oxide of at least one of the yttrium (Y) and the at least one rare earth element.
摘要翻译： 燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。 合金涂层（14）包括镍（Ni），铬（Cr），铝（Al）和钇（Y）。 此外，合金涂层包括钛（Ti），钽（Ta），钨（W）和铼（Re）中的至少一种。 合金涂层还包括至少一种稀土元素和至少一种钇（Y）和至少一种稀土元素的氧化物。
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公开(公告)号：US20080260571A1
公开(公告)日：2008-10-23
申请号：US11788301
申请日：2007-04-19
IPC分类号： C22C19/05
CPC分类号： C22C19/05
摘要： A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is well-suited for components of gas or steam turbine engines including blades and vanes.
摘要翻译： 公开了一种在氧化环境中形成氧化铬垢的镍基超级合金。 该合金在干燥或潮湿的气氛中在低于900℃的温度下提供良好的抗氧化性。 超级合金非常适合于包括叶片和叶片在内的气体或汽轮机发动机的部件。
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