公开(公告)号：US07094035B2

公开(公告)日：2006-08-22

申请号：US10775139

申请日：2004-02-11

Applicant: Thomas Kramer ,  Andreas Kuenzler ,  Mohamed Yousef Nazmy ,  Markus Staubli

Inventor： Thomas Kramer ,  Andreas Kuenzler ,  Mohamed Yousef Nazmy ,  Markus Staubli

IPC: F01D5/14

CPC classification number: F01D5/28 ,  F01D5/147 ,  F04D29/023 ,  F04D29/322 ,  F05C2201/0466 ,  F05D2300/171 ,  F05D2300/174 ,  F05D2300/18 ,  Y02T50/672 ,  Y02T50/673

Abstract: The invention relates to a hybrid blade (1) for thermal turbomachines, having an airfoil (2) made of a metallic material of a certain density, and having a blade root (3). It is characterized in that the blade root (3), compared with the airfoil (2), is made of a different metallic material having a lower density, and in that the airfoil (20) is connected to the blade root (3) in a positive-locking manner. The blade in this case is advantageously a compressor blade, in particular a high-pressure compressor blade, in which the airfoil (2) is made of a stainless CrNi steel and the blade root (3) is made of a high-temperature titanium alloy or an intermetallic gamma titanium aluminide alloy or an intermetallic orthorhombic titanium aluminide alloy.

Abstract translation: 本发明涉及一种用于热涡轮机的混合叶片（1），具有由一定密度的金属材料制成并具有叶根（3）的翼型（2）。 其特征在于，与翼型件（2）相比，叶片根部（3）由具有较低密度的不同的金属材料制成，并且翼型件（20）以与叶片根部（3）相连的方式连接到叶片根部 积极的方式。 在这种情况下，叶片有利地是压缩机叶片，特别是高压压缩机叶片，其中翼型件（2）由不锈钢CrNi钢制成，叶片根部（3）由高温钛合金制成 或金属间化合物γ铝铝合金或金属间斜方晶钛铝化合物。

公开(公告)号：US20060177312A1

公开(公告)日：2006-08-10

申请号：US11340510

申请日：2006-01-27

Applicant: Yasuoki Tomita ,  Kouji Watanabe ,  Masamitsu Okuzono ,  Masaki Ono

Inventor： Yasuoki Tomita ,  Kouji Watanabe ,  Masamitsu Okuzono ,  Masaki Ono

IPC: F01D11/00

CPC classification number: F01D5/081 ,  F01D5/22 ,  F01D11/008 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/29 ,  F05D2260/20 ,  Y02T50/671 ,  Y02T50/676 ,  Y10S416/50

Abstract: A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises rotor disc, a plurality of rotating blades being assembled so as to extend from the outer circumference of the rotor disc in a radial pattern, and sealing pins extending along the direction of the rotating shaft in the gaps between the platforms of the rotating blades being adjacent in circumferential direction. The sealing pins have a through-hole made therein, penetrating axially from one end surface to the other end surface.

Abstract translation: 提供了可以有效地抑制旋转叶片的振动的旋转叶片体。 旋转叶片主体包括转子盘，多个旋转叶片组装成以径向图案从转子盘的外圆周延伸，以及沿着旋转轴的方向在第二平台之间的间隙中延伸的密封销 旋转叶片在圆周方向上相邻。 密封销具有形成在其中的通孔，其从一个端面轴向穿透到另一端面。

公开(公告)号：US20060138195A1

公开(公告)日：2006-06-29

申请号：US11054635

申请日：2005-02-08

Applicant: Wayne Hasz ,  Nesim Abuaf ,  Robert Johnson ,  Ching-Pang Lee

Inventor： Wayne Hasz ,  Nesim Abuaf ,  Robert Johnson ,  Ching-Pang Lee

IPC: A47J36/02

CPC classification number: F28F13/18 ,  B23K35/30 ,  F01D5/147 ,  F01D5/186 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/23 ,  F05D2230/40 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/132 ,  F05D2300/172 ,  F05D2300/222 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12993

Abstract: A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.

Abstract translation: 描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。 首先将该紊乱施加到最终可以插入通道孔中的基底。 基板通常是由牺牲材料形成的棒或管。 在对基板施加了混浊之后，将基板插入到通孔中。 然后使用常规的加热技术将紊乱材料熔合到内表面。 然后可以通过各种技术从孔中去除牺牲衬底。 还描述了相关文章。

公开(公告)号：US20050220609A1

公开(公告)日：2005-10-06

申请号：US11097289

申请日：2005-04-04

Applicant: Christelle Foucher ,  Claude Lejars ,  Didier Riby

Inventor： Christelle Foucher ,  Claude Lejars ,  Didier Riby

IPC: F04D29/56 ,  F01D17/16 ,  F02C7/06 ,  F16C33/04

CPC classification number: F16C33/043 ,  F01D17/162 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/237 ,  F05D2300/21 ,  F05D2300/434

Abstract: The invention relates to a ceramic-based bushing for mounting in a turbomachine casing to provide a smooth bearing for a pivot of a variable-pitch vane. The bushing is constituted by a metal jacket and a ceramic ring secured to the inside wall of said jacket by brazing. The invention also provides a turbomachine compressor having variable-pitch stator vanes with pivots mounted in the casing by means of such bushings.

Abstract translation: 本发明涉及一种用于安装在涡轮机壳体中以提供用于可变桨距叶片的枢轴的平滑轴承的陶瓷基衬套。 衬套由金属护套和通过钎焊固定到所述护套的内壁的陶瓷环构成。 本发明还提供一种具有可变间距定子叶片的涡轮机压缩机，其具有通过这种衬套安装在壳体中的枢轴。

公开(公告)号：US20050186082A1

公开(公告)日：2005-08-25

申请号：US11062303

申请日：2005-02-18

Applicant: Andreas Kayser ,  Ivo Wolter

Inventor： Andreas Kayser ,  Ivo Wolter

IPC: F01D5/16 ,  F01D5/26 ,  F01D5/28 ,  F01D25/00 ,  F01D25/06 ,  F01D1/02

CPC classification number: F01D25/06 ,  F01D5/16 ,  F01D5/26 ,  F01D5/28 ,  F01D25/005 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/2102 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/222 ,  F05D2300/43 ,  F05D2300/50 ,  F05D2300/612 ,  F05D2300/615 ,  Y10S416/50

Abstract: The invention provides a high-temperature component for a turbomachine, in particular for a blade or vane having a main blade or vane part and a blade or vane root, the high-temperature component at least partially comprising, as base material, a porous material which is filled with a viscous filler and is surrounded by a solid layer.

Abstract translation: 本发明提供了一种用于涡轮机的高温部件，特别是用于具有主叶片或叶片部分以及叶片或叶片根部的叶片或叶片，所述高温部件至少部分地包括作为基材的多孔材料 其填充有粘性填料并被固体层包围。

公开(公告)号：US06910620B2

公开(公告)日：2005-06-28

申请号：US10271098

申请日：2002-10-15

Applicant: Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson ,  Ching-Pang Lee

Inventor： Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson ,  Ching-Pang Lee

IPC: F01D5/08 ,  B23K35/30 ,  C22C19/05 ,  C22C19/07 ,  C22C38/00 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F02C7/00 ,  F28F13/18 ,  B23K35/12 ,  B05D3/02 ,  B23K31/00

CPC classification number: F28F13/18 ,  B23K35/30 ,  F01D5/147 ,  F01D5/186 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/23 ,  F05D2230/40 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/132 ,  F05D2300/172 ,  F05D2300/222 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12993

Abstract: A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.

Abstract translation: 描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。 首先将该紊乱施加到最终可以插入通道孔中的基底。 基板通常是由牺牲材料形成的棒或管。 在对基板施加了混浊之后，将基板插入到通孔中。 然后使用常规的加热技术将紊乱材料熔合到内表面。 然后可以通过各种技术从孔中去除牺牲衬底。 还描述了相关文章。

公开(公告)号：US20050132717A1

公开(公告)日：2005-06-23

申请号：US10974973

申请日：2004-10-28

Applicant: Bertrand Saint Ramond ,  Manuel Silva ,  John Nicholls ,  Maxime Carlin

Inventor： Bertrand Saint Ramond ,  Manuel Silva ,  John Nicholls ,  Maxime Carlin

IPC: C22C5/04 ,  C22C19/05 ,  C23C14/00 ,  C23C14/06 ,  C23C16/00 ,  C23C28/00 ,  F01D5/00 ,  F01D5/28 ,  F02C7/00 ,  C23C14/32 ,  F02C3/04

CPC classification number: C23C28/3455 ,  C23C14/00 ,  C23C16/00 ,  C23C28/322 ,  C23C28/325 ,  C23C28/345 ,  C23C28/42 ,  F01D5/288 ,  F05C2201/0466 ,  F05D2300/121 ,  F05D2300/143 ,  F05D2300/173 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12736 ,  Y10T428/1275 ,  Y10T428/12875 ,  Y10T428/12931 ,  Y10T428/12944 ,  Y10T428/263

Abstract: A gas turbine part comprises a superalloy metal substrate, a bonding underlayer formed on the substrate and comprising an intermetallic compound of aluminum, nickel, and platinum, and a ceramic outer layer anchored on the alumina film formed on the bonding underlayer. The bonding underlayer essentially comprises an Ni—Pt—Al ternary system constituted by an aluminum-enriched α-NiPt type structure, in particular an Ni—Pt—Al ternary system having a composition NizPtyAlx in which z, y, and x are such that 0.05≦z≦0.40, 0.30≦y≦0.60, and 0.15≦x≦0.40.

Abstract translation: 燃气轮机部分包括超合金金属基板，形成在基板上的包含铝，镍和铂的金属间化合物的接合底层和锚定在形成在粘合底层上的氧化铝膜上的陶瓷外层。 键合底层基本上包括由富铝的α-NiPt型结构构成的Ni-Pt-Al三元体系，特别是Ni-Pt-Al三元体系，其具有组成为Ni <！ - SIPO

公开(公告)号：US06905559B2

公开(公告)日：2005-06-14

申请号：US10314083

申请日：2002-12-06

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

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

IPC: F01D5/28 ,  B22D21/00 ,  C22C5/04 ,  C22C19/05 ,  C22F1/00 ,  C22F1/10 ,  C30B11/00 ,  C30B29/52 ,  F02C7/00

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：US20050028364A1

公开(公告)日：2005-02-10

申请号：US10490273

申请日：2002-07-30

Applicant: Wolfgang Issler

Inventor： Wolfgang Issler

IPC: F02F3/00 ,  B21K1/18 ,  B21K25/00 ,  B23P15/10 ,  F02B23/06 ,  F02F3/04 ,  F02F3/12 ,  F16J1/01

CPC classification number: F02B23/0603 ,  B21K1/18 ,  B21K25/00 ,  B23P15/10 ,  F02B23/0696 ,  F02F3/045 ,  F02F3/12 ,  F02F2200/04 ,  F05C2201/0448 ,  F05C2201/0466 ,  Y02T10/125 ,  Y10T29/49249 ,  Y10T29/49252 ,  Y10T29/49256 ,  Y10T29/49263

Abstract: The invention relates to a method for producing a piston or piston head with a combustion relief (6) for an internal combustion engine. The aim of the invention is to easily and economically produce pistons having a reduced tendency to scale at the edge of the combustion relief. To this end, the piston is formed from a cylindrical unmachined part (1) made of steel, whereby the rod section has at least one front face (2). The method is characterized by the following steps: A) forming an annulary encircling recess (3) in the front face (2); B) introducing additional material (4) into the recess (3); connecting the additional material (4) to the steel of the unmachined part (1) in an at least partially non-positive manner; C) forging the unmachined part (1), which is formed according to steps A) and B), into a piston blank (5), and; D) machining the piston blank (5) into a piston (10) that is ready to be installed in an internal combustion engine.

Abstract translation: 本发明涉及一种用于制造具有用于内燃机的燃烧释放装置（6）的活塞或活塞头的方法。 本发明的目的是容易且经济地制造在燃烧浮雕的边缘处具有减小的结垢倾向的活塞。 为此，活塞由钢制的圆筒状的未加工部件（1）形成，杆部具有至少一个正面（2）。 该方法的特征在于以下步骤：A）在前表面（2）中形成一个环形凹槽（3）; B）将额外的材料（4）引入凹槽（3）中; 以至少部分非正的方式将附加材料（4）连接到未加工部件（1）的钢; C）将根据步骤A）和B）形成的未加工部件（1）锻造成活塞坯件（5），并且 D）将活塞坯件（5）加工成准备安装在内燃机中的活塞（10）。

公开(公告)号：US06827556B2

公开(公告)日：2004-12-07

申请号：US10379987

申请日：2003-03-05

Applicant: Volker Simon

Inventor： Volker Simon

IPC: F01D528

CPC classification number: F01D5/147 ,  B22F2998/00 ,  F01D5/28 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2260/203 ,  F05D2300/612 ,  B22F7/006

Abstract: A novel blade configuration does not exceed the permitted stresses for particular loads, especially as a result of centrifugal forces and which at the same time, allows the turbomachine to function with a high degree of efficiency. To this end, a moving blade for the turbomachine contains at least partially a cellular material, especially a foamed metal. The cellular material can be provided e.g. in the hollowed-out part of the moving blade.

Abstract translation: 新颖的叶片结构不会超过特定载荷的允许应力，特别是由于离心力而同时允许涡轮机以高效率起作用。 为此，用于涡轮机的移动叶片至少部分地包含多孔材料，特别是泡沫金属。 细胞材料可以例如提供。 在动叶片的中空部分。