公开(公告)号：US09056372B2

公开(公告)日：2015-06-16

申请号：US12902902

申请日：2010-10-12

Applicant: Warren Miglietti ,  John Roderick

Inventor： Warren Miglietti ,  John Roderick

IPC: B23P6/04 ,  B23K35/00 ,  B23K35/30 ,  C21D9/50 ,  C22C19/07 ,  C22F1/10 ,  C22F1/18 ,  F01D5/28 ,  F01D9/02 ,  C21D6/00

CPC classification number: B23P6/045 ,  B23K35/007 ,  B23K35/3046 ,  C21D6/007 ,  C21D9/50 ,  C22C19/07 ,  C22F1/10 ,  C22F1/18 ,  F01D5/286 ,  F01D9/02 ,  F05C2201/0463 ,  F05D2230/40 ,  F05D2300/13 ,  Y10T29/49318

Abstract: A method of extending the useable life of a gas turbine component fabricated from a cobalt-based alloy is disclosed. The method includes applying a rejuvenation process to the alloy where the alloy is placed in a protected atmosphere and heated to three different elevated temperatures and held at the elevated temperatures for approximately four hours each. Application of the rejuvenation process allows gas turbine components to be returned to service for at least one more service interval of approximately 24,000 operating hours.

Abstract translation: 公开了一种延长由钴基合金制成的燃气轮机部件的使用寿命的方法。 该方法包括将合金置于受保护的气氛中并加热到三种不同的升高温度并在高温下保持大约四个小时的合金应用复原过程。 复原过程的应用使得燃气轮机组件能够返回服务至少一个更多的服务间隔大约24,000个工作小时。

公开(公告)号：US20120288730A1

公开(公告)日：2012-11-15

申请号：US13521276

申请日：2011-01-10

Applicant: Friedhelm Schmitz ,  Werner Stamm

Inventor： Friedhelm Schmitz ,  Werner Stamm

IPC: C22C30/00 ,  B32B15/04

CPC classification number: C22C19/056 ,  C22C19/07 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2300/15 ,  Y02T50/67 ,  Y02T50/6765 ,  Y10T428/12618

Abstract: Known protective layers having a high Cr content, as well as silicon, have brittle phases that become additionally brittle under the influence of carbon during use. A protective layer that has the composition of 32% to 35% cobalt, 10% to 13% aluminum, 0.1% to 0.3% yttrium, and/or at least one equivalent metal from the group comprising scandium and the rate earth elements, 31% to 35% chromium, 0.1% to 0.5% silicon and the remainder nickel is provided.

Abstract translation: 具有高Cr含量的已知保护层以及硅具有在使用期间在碳的影响下变脆的脆性相。 保护层具有32％至35％的钴，10％至13％的铝，0.1％至0.3％的钇和/或至少一种当量的金属，来自包含钪和速率的土壤元素，31％ 至35％的铬，0.1％至0.5％的硅，并提供其余的镍。

公开(公告)号：US08021120B2

公开(公告)日：2011-09-20

申请号：US11918809

申请日：2006-01-20

Applicant: Albert Schrey ,  Gerhard Schwass ,  Armin de Lazzer

Inventor： Albert Schrey ,  Gerhard Schwass ,  Armin de Lazzer

IPC: F01D5/20

CPC classification number: F01D5/225 ,  F01D5/288 ,  F01D11/12 ,  F01D11/122 ,  F05C2201/0463 ,  F05D2230/232 ,  F05D2230/30 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2300/226 ,  F05D2300/228 ,  F05D2300/2284 ,  Y10T29/4932

Abstract: The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing.

Abstract translation: 本发明涉及具有形成在叶片的盘上的盖板的涡轮叶片。 本发明的目的是提供一种具有高水平效率的这种类型的涡轮叶片，其被设计用于在涡轮机，特别是蒸汽涡轮机中的特别可靠和安全的操作。 为此，本发明提供了将替代材料制成的保护层施加到盖板的远离叶片盘的表面。 对于与保护层相对的涡轮机部件，特别是密封条，可以具体地影响摩擦性能，从而在摩擦的情况下提供有利的紧急行驶性能。

公开(公告)号：US20100059572A1

公开(公告)日：2010-03-11

申请号：US12206886

申请日：2008-09-09

Applicant: John M. Sassatelli ,  John F. Nolan ,  Nicholas D. Porteous ,  Mark J. Passino, JR. ,  Gerald R. Crawmer ,  Carter S. Cook

Inventor： John M. Sassatelli ,  John F. Nolan ,  Nicholas D. Porteous ,  Mark J. Passino, JR. ,  Gerald R. Crawmer ,  Carter S. Cook

IPC: B23K31/02

CPC classification number: B23K9/044 ,  B23K2101/001 ,  B23K2103/04 ,  B23K2103/18 ,  B23K2103/26 ,  C21D9/50 ,  C22C19/00 ,  F01D5/005 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/31 ,  F05D2230/232 ,  F05D2300/11 ,  F05D2300/131 ,  F05D2300/132

Abstract: A method for repairing a steel alloy article, and an article repaired thereby, is provided and comprises the steps of depositing at least a first weld repair layer on a surface of the article so as to form a heat affected zone in the article beneath the surface. Locally heat treating the first weld repair layer and at least a portion of the heat affected zone adjacent the first weld repair layer at a temperature above the critical A1 temperature of the steel alloy article. Depositing at least one additional weld repair layer on the first weld repair layer without forming additional heat affected zone in the surface of the article. The first weld repair layer and the at least one additional weld repair layer are comprised of a material chosen from the group consisting of nickel chromium—iron alloys, cobalt base alloys, ERNiCr-3, ENiCrFe-3, ERNiCrMo-3, ERNiFeCr-2, ERCoCr-A, ERCoCr-E, CrMo alloys and CrMoV alloys. The article can be placed in service without a post-weld heat treatment of the additional weld repair layer following the step of depositing the additional weld repair layer.

Abstract translation: 提供了修复钢合金制品的方法和由此修补的制品，并且包括以下步骤：在制品的表面上沉积至少第一焊接修复层，以便在制品下面形成热影响区 。 在高于钢合金制品的临界Al温度的温度下，局部热处理第一焊接修复层和与第一焊接修复层相邻的热影响区的至少一部分。 在第一焊接修复层上沉积至少一个附加的焊接修复层，而不在制品的表面中形成额外的热影响区。 第一焊接修复层和至少一个另外的焊接修复层由选自镍铬铁合金，钴基合金，ERNiCr-3，ENiCrFe-3，ERNiCrMo-3，ERNiFeCr-2的材料组成 ，ERCoCr-A，ERCoCr-E，CrMo合金和CrMoV合金。 在附加的焊接修复层的沉积步骤之后，可以在不进行附加焊接修复层的焊后热处理的情况下使用该制品。

公开(公告)号：US07514157B2

公开(公告)日：2009-04-07

申请号：US10558648

申请日：2004-02-25

Applicant: Yasuhiro Aoki ,  Akihiro Sato

Inventor： Yasuhiro Aoki ,  Akihiro Sato

IPC: B05D3/00 ,  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：US07510195B2

公开(公告)日：2009-03-31

申请号：US10719223

申请日：2003-11-21

Applicant: Yoshio Usui ,  Tom Iles ,  Trung N. Tran

Inventor： Yoshio Usui ,  Tom Iles ,  Trung N. Tran

IPC: F16J9/14 ,  F16J9/26 ,  F02F5/00

CPC classification number: F04B39/0005 ,  F05C2201/0406 ,  F05C2201/0463 ,  F05C2203/0808 ,  F05C2203/0826 ,  F16J9/14 ,  F16J9/20 ,  F16J9/26

Abstract: A piston ring for use at temperatures above 350° F. at pressures greater than or equal to about 2000 psi, comprising a gap having a gap width about 1.4 to about 2.0 times greater than a thickness of the piston ring; a height about 4.5 to about 6.4 times larger than the thickness, and a leading edge characterized by an arc having a radius of curvature of less than or equal to about 4 times the height. The piston ring may be formed of a material comprising cobalt, chromium, tungsten, and carbon. A gas compressor and method of sealing a piston using the above piston ring is also provided for.

Abstract translation: 一种在大于或等于约2000psi的压力下在高于350°F的温度下使用的活塞环，包括间隙宽度比活塞环厚度大约1.4至大约2.0倍的间隙; 高度比该厚度大约4.5至大约6.4倍的高度，以及具有小于或等于大约4倍的曲率半径的弧形的前缘。 活塞环可以由包括钴，铬，钨和碳的材料形成。 还提供了一种气体压缩机和使用上述活塞环密封活塞的方法。

公开(公告)号：US20090075101A1

公开(公告)日：2009-03-19

申请号：US12194577

申请日：2008-08-20

Applicant: Anand A. Kulkarni ,  Allister W. James ,  Douglas J. Arrell

Inventor： Anand A. Kulkarni ,  Allister W. James ,  Douglas J. Arrell

IPC: B32B15/00 ,  B32B15/04 ,  B32B15/01 ,  B05D1/02

CPC classification number: C23C30/00 ,  B22F1/0085 ,  B22F1/0088 ,  B22F9/082 ,  B22F2998/10 ,  B22F2999/00 ,  C22C1/002 ,  C23C4/073 ,  C23C4/10 ,  C23C24/04 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  C23C28/347 ,  F01D5/288 ,  F01D25/007 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/15 ,  Y10T428/12535 ,  Y10T428/12611 ,  Y10T428/1266 ,  Y10T428/31678 ,  B22F2201/01 ,  B22F2201/03 ,  C23C24/00

Abstract: 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 a first amount, by weight percent, of cobalt (Co) and a second amount, by weight percent, of nickel (Ni), the first amount being greater than the second amount. The alloy coating further includes chromium (Cr), aluminum (Al), at least one rare earth element, and an oxide of the at least one rare earth element.

Abstract translation: 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）包括第一量的重量百分比的钴（Co）和第二量的以镍（Ni）的重量百分比计的第一量，第一量大于第二量。 合金涂层还包括铬（Cr），铝（Al），至少一种稀土元素和至少一种稀土元素的氧化物。

公开(公告)号：US07435056B2

公开(公告)日：2008-10-14

申请号：US11413755

申请日：2006-04-28

Applicant: Laurence D. N. Liston

Inventor： Laurence D. N. Liston

IPC: F01D9/00

CPC classification number: F01D5/288 ,  F01D5/282 ,  F01D5/284 ,  F01D5/286 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/21 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2263 ,  F05D2300/433 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.

Abstract translation: 本发明提供一种涡轮风扇发动机，其包括其中包含的复合定子叶片的前缘侵蚀保护。 复合定子叶片由前缘，后缘，凹面和凸面限定。 叶片通常由石墨纤维和芳族聚酰胺纤维编织预制件形成，其与环氧树脂基质树脂或其它高温基质树脂层压。 在模制过程中将金属丝网屏蔽嵌入到环氧树脂基质树脂前缘的最外表面中。 由复合定子叶片的前缘将一个由侵蚀保护材料组成的锥形侵蚀保护层施加到丝网筛上，有助于保护定子叶片的前缘免受碎片和污染物的影响，包括操作流体，灰尘和 可能在通过涡轮风扇发动机的空气流中携带的沙子以及腐蚀性的操作环境。

公开(公告)号：US07300708B2

公开(公告)日：2007-11-27

申请号：US10801843

申请日：2004-03-16

Applicant: Michael Francis Xavier Gigliotti, Jr. ,  Canan Uslu Hardwicke ,  Liang Jiang ,  John William Short ,  Don Mark Lipkin ,  Jonathan Paul Blank ,  Krishnamurthy Anand

Inventor： Michael Francis Xavier Gigliotti, Jr. ,  Canan Uslu Hardwicke ,  Liang Jiang ,  John William Short ,  Don Mark Lipkin ,  Jonathan Paul Blank ,  Krishnamurthy Anand

IPC: B32B15/04 ,  B32B18/00

CPC classification number: B23K20/08 ,  F01D5/28 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/31 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/501 ,  F05D2300/505 ,  F05D2300/611 ,  Y10S420/902 ,  Y10T428/12493 ,  Y10T428/12611 ,  Y10T428/12806 ,  Y10T428/12944

Abstract: An erosion resistant protective structure for a turbine engine component comprises a shape memory alloy. The shape memory alloy includes nickel-titanium based alloys, indium-titanium based alloys, nickel-aluminum based alloys, nickel-gallium based alloys, copper based alloys, gold-cadmium based alloys, iron-platinum based alloys, iron-palladium based alloys, silver-cadmium based alloys, indium-cadmium based alloys, manganese-copper based alloys, ruthenium-niobium based alloys, ruthenium-tantalum based alloys, titanium based alloys, iron-based alloys, or combinations comprising at least one of the foregoing alloys. Also, disclosed herein are methods for forming the shape memory alloy onto turbine component.

Abstract translation: 用于涡轮发动机部件的抗侵蚀保​​护结构包括形状记忆合金。 形状记忆合金包括镍 - 钛基合金，铟 - 钛基合金，镍 - 铝基合金，镍 - 镓基合金，铜基合金，金 - 镉基合金，铁 - 铂基合金，铁 - 钯基合金 银镉基合金，铟镉基合金，锰 - 铜基合金，钌 - 铌基合金，钌 - 钽基合金，钛基合金，铁基合金或包含至少一种上述合金的组合 。 此外，本文公开的是将形状记忆合金形成在涡轮部件上的方法。

公开(公告)号：US20070201984A1

公开(公告)日：2007-08-30

申请号：US11413755

申请日：2006-04-28

Applicant: Laurence Liston

Inventor： Laurence Liston

IPC: B63H1/26

CPC classification number: F01D5/288 ,  F01D5/282 ,  F01D5/284 ,  F01D5/286 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/21 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2263 ,  F05D2300/433 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.

Abstract translation: 本发明提供一种涡轮风扇发动机，其包括其中包含的复合定子叶片的前缘侵蚀保护。 复合定子叶片由前缘，后缘，凹面和凸面限定。 叶片通常由石墨纤维和芳族聚酰胺纤维编织预制件形成，其与环氧树脂基质树脂或其它高温基质树脂层压。 在模制过程中将金属丝网屏蔽嵌入到环氧树脂基质树脂前缘的最外表面中。 由复合定子叶片的前缘将一个由侵蚀保护材料组成的锥形侵蚀保护层施加到丝网筛上，有助于保护定子叶片的前缘免受碎片和污染物的影响，包括操作流体，灰尘和 可能在通过涡轮风扇发动机的空气流中携带的沙子以及腐蚀性的操作环境。