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    Methods and apparatus for cooling gas turbine nozzles
    4.
    发明授权
    Methods and apparatus for cooling gas turbine nozzles 有权
    用于冷却燃气轮机喷嘴的方法和装置

    公开(公告)号：US06609880B2

    公开(公告)日：2003-08-26

    申请号：US09998835

    申请日：2001-11-15

    申请人： Andrew Charles Powis ,  Jonathan Philip Clarke ,  Judd Dodge Tressler

    发明人： Andrew Charles Powis ,  Jonathan Philip Clarke ,  Judd Dodge Tressler

    IPC分类号： F10D906

    CPC分类号： F01D25/12 ,  F01D5/189 ,  F01D9/02 ,  F05D2260/201 ,  Y02T50/676

    摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more airfoil vane sidewall cooling than the second plurality of cooling openings.

    摘要翻译： 用于组装燃气涡轮发动机的涡轮喷嘴的方法有利于提高涡轮喷嘴的冷却效率。 该方法包括提供一个中空的双层结构，该空心双层结构包括一个由至少一个平台联接的先导翼型件和后翼型件，其中每个翼型件包括在相应的前缘和后缘之间延伸的第一侧壁和第二侧壁。 该方法还包括将插入件插入到至少一个翼型件中，其中插入件包括第一侧壁，第一侧壁包括第一多个冷却开口，第一多个冷却开口延伸穿过其中，第二侧壁包括延伸穿过其中的第二多个冷却开口， 第一多个冷却开口有助于比第二多个冷却开口更多的翼型叶片侧壁冷却。

    Methods and apparatus for cooling gas turbine nozzles
    5.
    再颁专利
    Methods and apparatus for cooling gas turbine nozzles 有权
    用于冷却燃气轮机喷嘴的方法和装置

    公开(公告)号：USRE40658E1

    公开(公告)日：2009-03-10

    申请号：US11287565

    申请日：2005-11-23

    申请人： Andrew Charles Powis ,  Jonathan Philip Clarke ,  Judd Dodge Tressler

    发明人： Andrew Charles Powis ,  Jonathan Philip Clarke ,  Judd Dodge Tressler

    IPC分类号： F01D9/06

    CPC分类号： F01D25/12 ,  F01D5/189 ,  F01D9/02 ,  F05D2260/201 ,  Y02T50/676

    摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.

    摘要翻译： 用于组装燃气涡轮发动机的涡轮喷嘴的方法有利于提高涡轮喷嘴的冷却效率。 该方法包括提供一个中空的双层结构，该空心双层结构包括一个由至少一个平台联接的先导翼型件和后翼型件，其中每个翼型件包括在相应的前缘和后缘之间延伸的第一侧壁和第二侧壁。 该方法还包括将插入件插入到至少一个翼型件中，其中插入件包括第一侧壁，第一侧壁包括第一多个冷却开口，第一多个冷却开口延伸穿过其中，第二侧壁包括延伸穿过其中的第二多个冷却开口， 第一多个冷却开口有助于翼型件比第二多个冷却开口更多的冷却。

    Turbine shroud asymmetrical cooling elements
    6.
    发明授权
    Turbine shroud asymmetrical cooling elements 有权
    涡轮罩不对称冷却元件

    公开(公告)号：US07147432B2

    公开(公告)日：2006-12-12

    申请号：US10720430

    申请日：2003-11-24

    申请人： Cedric Carlton Lowe ,  Andrew Charles Powis ,  Jonathan Philip Clarke

    发明人： Cedric Carlton Lowe ,  Andrew Charles Powis ,  Jonathan Philip Clarke

    IPC分类号： F01D25/12 ,  F01D25/14

    CPC分类号： F01D11/08 ,  F01D9/04 ,  F01D25/12 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676 ,  Y10S165/908

    摘要： A turbine shroud assembly asymmetrical cooling element such as a shroud segment or a baffle includes an arcuate panel. The panel has a plurality of cooling apertures extending through the panel and an axially extending midline of the panel parallel to an axis of rotation of the arcuate panel. A symmetric portion of the cooling apertures have a symmetrical density of aperture inlets that is symmetric with respect to the axially extending midline. An asymmetric portion of the cooling apertures have an asymmetrical density of aperture inlets that is asymmetric with respect to the axially extending midline. One exemplary cooling element includes a high density area of the cooling apertures in the asymmetric portion having a higher density of aperture inlets than in the symmetric portion. A low density area of the cooling apertures in the asymmetric portion has a lower density of aperture inlets than in the symmetric portion of the cooling apertures.

    摘要翻译： 涡轮机罩组件诸如护罩段或挡板的不对称冷却元件包括弓形面板。 面板具有延伸穿过面板的多个冷却孔，并且面板的轴向延伸的中线平行于弧形面板的旋转轴线。 冷却孔的对称部分具有相对于轴向延伸的中线对称的孔径入口的对称密度。 冷却孔的不对称部分具有相对于轴向延伸中线不对称的孔入口的不对称密度。 一个示例性的冷却元件包括不对称部分中的冷却孔的高密度区域，其具有比在对称部分中更高密度的孔入口。 不对称部分中的冷却孔的低密度区域具有比在冷却孔的对称部分中更小的孔入口密度。

    Methods and apparatus for cooling gas turbine nozzles
    7.
    发明授权
    Methods and apparatus for cooling gas turbine nozzles 有权

    公开(公告)号：US06652220B2

    公开(公告)日：2003-11-25

    申请号：US09998947

    申请日：2001-11-15

    申请人： Andrew Charles Powis ,  Jonathan Philip Clarke ,  Judd Dodge Tressler

    发明人： Andrew Charles Powis ,  Jonathan Philip Clarke ,  Judd Dodge Tressler

    IPC分类号： F01D906

    CPC分类号： F01D25/12 ,  F01D5/189 ,  F01D9/02 ,  F05D2260/201 ,  Y02T50/676

    摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.

    Turbine blade frequency tuned pin bank
    8.
    发明授权
    Turbine blade frequency tuned pin bank 有权
    涡轮叶片频率调谐针库

    公开(公告)号：US07008179B2

    公开(公告)日：2006-03-07

    申请号：US10737428

    申请日：2003-12-16

    申请人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Mark Edward Stegemiller ,  Hardev Singh ,  Steven Robert Brassfield

    发明人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Mark Edward Stegemiller ,  Hardev Singh ,  Steven Robert Brassfield

    IPC分类号： F01D25/36

    CPC分类号： F01D5/16 ,  F05D2260/96 ,  Y10S416/50

    摘要： A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.

    摘要翻译： 燃气涡轮发动机涡轮机叶片包括从叶片根部径向延伸到径向外部翼型端头的中空翼型件。 翼型件包括翼型件外壁，其具有横向间隔开的压力和抽吸侧壁，其沿翼型间隔开的前缘和后缘相交。 翼型件内的径向延伸的冷却空气供应通道包括与压力侧和侧壁之间横向间隔并横向延伸的一排销。 调整销的组，使得与发动机的发动机强制驱动模式相关联的叶片的固有频率足够远离稳态发动机工作频率，以便在稳态发动机操作期间基本上避免叶片的固有频率共振。 引脚的组合由冷却空气供应通道中的销的位置调节。

    Methods and systems for cooling gas turbine engine airfoils
    9.
    发明授权
    Methods and systems for cooling gas turbine engine airfoils 有权
    用于冷却燃气涡轮发动机翼型的方法和系统

    公开(公告)号：US06561758B2

    公开(公告)日：2003-05-13

    申请号：US09844206

    申请日：2001-04-27

    申请人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Brian Alan Norton

    发明人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Brian Alan Norton

    IPC分类号： F01D518

    CPC分类号： F01D5/20 ,  F01D5/186 ,  Y10T29/49341

    摘要： A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The sidewalls define a cooling cavity that includes at least a leading edge chamber bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region, a throat, and a passageway region connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.

    摘要翻译： 燃气涡轮发动机包括包括翼型的转子叶片，其有助于减少由于翼型后缘切割引起的制造损失。 每个翼型件包括在前缘和后缘连接的第一和第二侧壁。 侧壁限定了一个冷却腔，其包括由侧壁和翼型件前缘限定的至少一个前缘室，以及由侧壁和翼型后缘界定的后缘室。 冷却腔后缘室包括尖端区域，喉部和流动连通地连通的通道区域，使得喉部位于尖端区域和通道区域之间。 此外，尖端区域由翼面尖端限制，并且从咽喉分开延伸，使得尖端区域的宽度大于喉部的宽度。

    Coated article and method for repairing a coated surface
    10.
    发明授权
    Coated article and method for repairing a coated surface 有权

    公开(公告)号：US07093335B2

    公开(公告)日：2006-08-22

    申请号：US10189087

    申请日：2002-07-03

    申请人： Jeffrey Allen Conner ,  Roger Dale Wustman ,  Jonathan Philip Clarke

    发明人： Jeffrey Allen Conner ,  Roger Dale Wustman ,  Jonathan Philip Clarke

    IPC分类号： B23P6/00

    CPC分类号： C23C28/021 ,  C23C4/02 ,  C23C10/02 ,  C23C10/58 ,  C23C28/028 ,  Y10T29/49718 ,  Y10T29/49734 ,  Y10T29/49746 ,  Y10T29/49885 ,  Y10T29/49982 ,  Y10T428/12611 ,  Y10T428/12875 ,  Y10T428/12931 ,  Y10T428/12944

    摘要： A method is provided for repairing a surface portion of an article including a metallic environmental resistant coating on a substrate. The coating includes a coating outer portion bonded with the substrate through a diffusion zone that includes at least one feature, for example Al and/or an intermetallic phase, in an amount detrimental to application of a metallic replacement coating and/or repair of the article. The method comprises removing the coating outer portion to expose a surface of the diffusion zone. The substrate and the diffusion zone are heated at a temperature and for a time sufficient to diffuse and/or dissolve at least a portion of the at least one feature in the exposed surface and in a portion of the diffusion zone beneath the exposed surface to a level below the detrimental amount. This provides a replacement surface portion integral with diffusion zone. Then a metallic replacement coating outer portion is applied to the replacement surface portion. Provided is a coated article comprising a substrate and a metallic environmental resistant coating bonded with the substrate. The coating comprises an inner modified portion of the substrate integral with the substrate, an outer diffusion zone integral with the inner portion, and a metallic environmental resistant coating outer portion integral with the outer diffusion zone. In some forms, the coated article includes a thermal barrier coating over the metallic coating outer portion.