公开(公告)号：US07389991B2

公开(公告)日：2008-06-24

申请号：US11236243

申请日：2005-09-27

Applicant: Vincent T. Riggi, Jr. ,  Ronald A. Riggi

Inventor： Vincent T. Riggi, Jr. ,  Ronald A. Riggi

IPC: F16J15/16

CPC classification number: F16J15/3288 ,  F01D11/00 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/71 ,  F05D2300/601 ,  F16J15/3284

Abstract: A leakage seal for use in a gas path between two relatively rotatable members of a gas turbine comprises a foil layer and a cloth layer. The foil layer has two expansive surfaces, a single one of which is covered by the cloth layer. The leakage seal has a proximal end, a distal end, and a generally flat region between the proximal and distal ends. The proximal end is attached to an associated one of the turbine members. The distal end diverges from the generally flat region so as to define a curved hook, along which the cloth portion is wrapped over the foil layer, when the distal end is viewed in cross-section.

Abstract translation: 用于燃气轮机的两个相对旋转的构件之间的气体路径中的泄漏密封件包括箔层和布层。 箔层具有两个膨胀表面，其中一个被布层覆盖。 泄漏密封件具有近端，远端以及近端和远端之间的大致平坦的区域。 近端附接到相关联的一个涡轮机构件。 远端从大体上平坦的区域分开，以限定弯曲的钩子，当横截面看到远端时，布料部分沿着该部分被卷绕在箔层上。

公开(公告)号：US20080056888A1

公开(公告)日：2008-03-06

申请号：US11515101

申请日：2006-09-01

Applicant: Nagendra Somanath ,  Keshava B. Kumar

Inventor： Nagendra Somanath ,  Keshava B. Kumar

IPC: F01D25/16

CPC classification number: F01D9/041 ,  F01D5/147 ,  F01D5/187 ,  F01D25/162 ,  F05C2201/0463 ,  F05D2240/12 ,  F05D2300/133 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning a flow of working fluid and an internal spar spaced from the aerodynamic shell by an air gap and reinforced by stiffeners.

Abstract translation: 用于燃气涡轮机飞机发动机的引导叶片包括用于转动工作流体流的空气动力学外壳和通过气隙与空气动力学外壳间隔开的内部翼梁，并由加强筋加强。

公开(公告)号：US20070069478A1

公开(公告)日：2007-03-29

申请号：US11236243

申请日：2005-09-27

Applicant: Vincent Riggi ,  Ronald Riggi

Inventor： Vincent Riggi ,  Ronald Riggi

IPC: F16J15/00

CPC classification number: F16J15/3288 ,  F01D11/00 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/71 ,  F05D2300/601 ,  F16J15/3284

Abstract: A leakage seal for use in a gas path between two relatively rotatable members of a gas turbine comprises a foil layer and a cloth layer. The foil layer has two expansive surfaces, a single one of which is covered by the cloth layer. The leakage seal has a proximal end, a distal end, and a generally flat region between the proximal and distal ends. The proximal end is attached to an associated one of the turbine members. The distal end diverges from the generally flat region so as to define a curved hook, along which the cloth portion is wrapped over the foil layer, when the distal end is viewed in cross-section.

Abstract translation: 用于燃气轮机的两个相对旋转的构件之间的气体路径中的泄漏密封件包括箔层和布层。 箔层具有两个膨胀表面，其中一个被布层覆盖。 泄漏密封件具有近端，远端以及近端和远端之间的大致平坦的区域。 近端附接到相关联的一个涡轮机构件。 远端从大体上平坦的区域分开，以限定弯曲的钩子，当横截面看到远端时，布料部分沿着该部分被卷绕在箔层上。

公开(公告)号：US20070026256A1

公开(公告)日：2007-02-01

申请号：US10558648

申请日：2004-02-25

Applicant: Yasuhiro Aoki ,  Akihiro Sato

Inventor： Yasuhiro Aoki ,  Akihiro Sato

IPC: B32B15/00 ,  B32B15/20 ,  B32B15/01

CPC classification number: C23C10/02 ,  F01D5/288 ,  F05C2201/0463 ,  F05D2300/132 ,  Y02T50/671 ,  Y10T428/12847 ,  Y10T428/12861 ,  Y10T428/1291 ,  Y10T428/12931 ,  Y10T428/12944

Abstract: A reaction control turbine blade is formed by applying a reaction control material to the surface of an Ni-base superalloy before applying aluminum diffusion coating to the Ni-base superalloy. The reaction control material is Co, Cr or Ru, or an alloy of which main component is selected from a group consisting of Co, Cr, Ru. Thereby, it is possible to enhance the oxidation resistance of the Ni-base superalloy, and to control formation of a secondary reaction zone.

Abstract translation: 在向Ni基超级合金施加铝扩散涂层之前，通过将反应控制材料施加到Ni基超级合金的表面上来形成反应控制涡轮叶片。 反应控制材料是Co，Cr或Ru，或者主要成分选自Co，Cr，Ru的合金。 由此，可以提高Ni基超合金的抗氧化性，并且可以控制二次反应区的形成。

公开(公告)号：US20060285974A1

公开(公告)日：2006-12-21

申请号：US11160272

申请日：2005-06-16

Applicant: Ronald Bunker ,  Gary Itzel

Inventor： Ronald Bunker ,  Gary Itzel

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

Abstract: A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side.

Abstract translation: 用于涡轮机桶的顶盖件。 尖端盖可以包括冷侧和位于冷侧的多个销。

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。