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：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。

公开(公告)号：US20040072014A1

公开(公告)日：2004-04-15

申请号：US10271098

申请日：2002-10-15

Applicant: General Electric Company

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

IPC: B32B001/06 ,  B32B001/08 ,  B32B015/02

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：US20030121412A1

公开(公告)日：2003-07-03

申请号：US10316418

申请日：2002-12-11

Inventor： Manabu Sugiura ,  Takahiro Sugioka ,  Shino Ohkubo ,  Akira Onoda ,  Tomohiro Murakami ,  Minoru Mera

IPC: F01B003/00

CPC classification number: F04B27/0886 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05C2201/903 ,  F05C2253/12

Abstract: A shoe for a swash plate type compressor disposed between a swash plate and a corresponding one of a plurality of pistons, the shoe being characterized by comprising: a base body formed of an aluminum alloy; and a metal plating film which covers at least a portion of a surface of the base body.

Abstract translation: 一种用于旋转斜盘式压缩机的鞋，其设置在斜盘和多个活塞中的相应一个活塞之间，所述鞋的特征在于包括：由铝合金形成的基体; 以及覆盖基体的表面的至少一部分的金属电镀膜。

公开(公告)号：US20030082048A1

公开(公告)日：2003-05-01

申请号：US09682814

申请日：2001-10-22

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: F01D005/28

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.

公开(公告)号：US20010022934A1

公开(公告)日：2001-09-20

申请号：US09769749

申请日：2001-01-26

Inventor： Thomas Charles Mashey

IPC: F01D005/08 ,  F01D005/14

CPC classification number: C23C28/321 ,  C23C28/34 ,  C23C28/347 ,  F01D5/084 ,  F01D9/06 ,  F01D25/18 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/509 ,  F05D2300/611 ,  F16L58/08 ,  F16L58/14

Abstract: Cooling steam delivery tubes extend axially along the outer rim of a gas turbine rotor for supplying cooling steam to and returning spent cooling steam from the turbine buckets. Because of the high friction forces at the interface of the tubes and supporting elements due to rotor rotation, a low coefficient of friction coating is provided at the interface of the tubes and support elements. On each surface, a first coating of a cobalt-based alloy is sprayed onto the surface at high temperature. A portion of the first coating is machined off to provide a smooth, hard surface. A second ceramic-based solid film lubricant is sprayed onto the first coating. By reducing the resistance to axial displacement of the tubes relative to the supporting elements due to thermal expansion, the service life of the tubes is substantially extended.

Abstract translation: 冷却蒸汽输送管沿着燃气涡轮机转子的外缘轴向延伸，用于将冷却蒸汽供给并从涡轮机叶返回废冷却蒸汽。 由于由于转子旋转而在管和支撑元件的界面处的高摩擦力，所以在管和支撑元件的界面处提供了低摩擦系数涂层。 在每个表面上，钴基合金的第一涂层在高温下喷涂到表面上。 第一涂层的一部分被加工以提供光滑的硬表面。 将第二陶瓷基固体膜润滑剂喷涂到第一涂层上。 通过由于热膨胀减小管相对于支撑元件的轴向位移的阻力，管的使用寿命显着延长。

公开(公告)号：US5960249A

公开(公告)日：1999-09-28

申请号：US35802

申请日：1998-03-06

Applicant: Ann Melinda Ritter ,  Paul Leonard Dupree ,  Melvin Robert Jackson ,  Donald Norman Wemple, Jr.

Inventor： Ann Melinda Ritter ,  Paul Leonard Dupree ,  Melvin Robert Jackson ,  Donald Norman Wemple, Jr.

IPC: B22F3/12 ,  B22F5/04 ,  B22F7/06 ,  B23P15/04 ,  F01D5/18 ,  F01D5/28 ,  G22B7/00

CPC classification number: F01D5/18 ,  B22F3/1208 ,  B22F5/04 ,  B22F7/062 ,  B23P15/04 ,  F01D5/28 ,  F01D5/282 ,  B22F2998/00 ,  B22F2998/10 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/20 ,  F05D2230/22 ,  F05D2300/603 ,  Y10T428/12028

Abstract: A method for forming an exterior surface of a high-temperature component, such as a blade or vane of a gas turbine engine. The method entails forming a shell by a powder metallurgy technique that yields an airfoil whose composition can be readily tailored for the particular service conditions of the component. The method generally entails providing a pair of inner and outer mold members that form a cavity therebetween. One or more powders and any desired reinforcement material are then placed in the cavity and then consolidated at an elevated temperature and pressure in a non-oxidizing atmosphere. Thereafter, at least the outer mold member is removed to expose the consolidated powder structure. By appropriately shaping the mold members to tailor the shape of the cavity, the consolidated powder structure has the desired shape for the exterior shell of a component, such that subsequent processing of the component does not require substantially altering the configuration of the exterior shell. The airfoil can be produced as a free-standing article or produced directly on a mandrel that subsequently forms the interior structure of the component. In one embodiment, an airfoil is configured to have double walls through which cooling air flows.

Abstract translation: 一种用于形成诸如燃气轮机的叶片或叶片的高温部件的外表面的方法。 该方法需要通过粉末冶金技术形成壳体，该技术产生的翼型件的组合可以容易地根据部件的特定使用条件进行定制。 该方法通常需要提供一对在其间形成空腔的内部和外部模具构件。 然后将一种或多种粉末和任何所需的增强材料置于空腔中，然后在非氧化性气氛中在升高的温度和压力下固化。 此后，至少移除外模构件以暴露固结的粉末结构。 通过适当地成型模具以适应空腔的形状，固结的粉末结构具有用于组件的外壳的期望的形状，使得组件的后续处理不需要基本上改变外壳的构造。 翼型件可以作为独立制品生产，或直接制造在随后形成部件的内部结构的心轴上。 在一个实施例中，翼型构造成具有双壁，冷却空气流过该壁。

公开(公告)号：US2873733A

公开(公告)日：1959-02-17

申请号：US56971756

申请日：1956-03-06

Applicant: BYRON HICKS JARVIS

Inventor： BYRON HICKS JARVIS

IPC: F02B77/02

CPC classification number: F02B77/02 ,  F05C2201/021 ,  F05C2201/023 ,  F05C2201/0463 ,  F05C2201/0472 ,  F05C2201/0475 ,  F05C2201/0487 ,  F05C2201/0493