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公开(公告)号：US07147432B2
公开(公告)日：2006-12-12
申请号：US10720430
申请日：2003-11-24
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。
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公开(公告)号：US06609880B2
公开(公告)日：2003-08-26
申请号：US09998835
申请日：2001-11-15
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。
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公开(公告)号：US06932568B2
公开(公告)日：2005-08-23
申请号：US10375441
申请日：2003-02-27
申请人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D9/041 , B22C21/14 , E05Y2900/402 , F01D5/189 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , F05D2260/30 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.
摘要翻译： 涡轮喷嘴段包括至少一个在径向外带段和内带段之间径向延伸的中空翼型件，在外带段的后端处的顺时针端部上的顺时针打开的钩子，以及逆时针方向的逆时针方向的开口钩 在外带段的后端。 涡轮喷嘴段的示例性实施例包括从外带段径向向外延伸的负载停止。 至少一个面向前的负载面处于外带段处的喷嘴段的后端。 顺时针打开的钩子是C形的，逆时针打开的钩子是一个shiplap钩子。 涡轮喷嘴段的另一个实施例仅具有一个中空翼型件，其翼型壁围绕通过在翼型件壁的压力侧和抽吸侧之间延伸的分叉肋分成前部和后部空腔的分叉空腔。
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公开(公告)号：USRE40658E1
公开(公告)日：2009-03-10
申请号：US11287565
申请日：2005-11-23
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。
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公开(公告)号：US06652220B2
公开(公告)日：2003-11-25
申请号：US09998947
申请日：2001-11-15
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.
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公开(公告)号：US07008185B2
公开(公告)日：2006-03-07
申请号：US10375415
申请日：2003-02-27
申请人： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D5/189 , F01D9/041 , F05D2240/81 , F05D2250/70 , F05D2260/201 , F05D2260/30 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.
摘要翻译： 涡轮喷嘴分叉冲击挡板包括轴向前后空间，其间具有间隙，冲击孔分别通过前后舱的前后挡板壁和与前室和后室流体连通的增压室。 分叉式冲击挡板的示例性实施例还包括一个单独的冷却空气入口，该冷却空气入口封闭在包围增压室的增压室内。 密封板安装在密封室之间并密封到增压室外壳和前后室。 密封板具有分别设置在增压室和前后室之间的前后入口孔。 前端和后端板盖住前后室的径向内端。 前端板中的出口孔具有穿过其设置的级间密封腔供给管。
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7.发明授权Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity 有权燃气涡轮发动机涡轮喷嘴段具有单个空心叶片，其具有分叉腔公开(公告)号：US06969233B2
公开(公告)日：2005-11-29
申请号：US10375585
申请日：2003-02-27
申请人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D5/189 , B22C21/14 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.
摘要翻译： 涡轮喷嘴段包括在径向外部段和内部带段之间径向延伸的单个中空翼型件。 翼型件具有翼型壁，其压力和吸力侧面在翼型的前缘和后缘之间轴向延伸。 翼型壁围绕分叉的空腔并且分叉肋延伸穿过分叉的空腔，并且在翼型壁的压力和吸力侧之间延伸，将分叉腔分成前后空腔。 加强筋从外带段的径向外表面径向向外延伸，并且从外带段的压力侧前角轴向和周向延伸到分叉肋。 外带和内带段，分叉肋和加强筋是整体的，由一体式单件铸件制成。
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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。
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公开(公告)号：US06561758B2
公开(公告)日：2003-05-13
申请号：US09844206
申请日：2001-04-27
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。
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公开(公告)号：US07093335B2
公开(公告)日：2006-08-22
申请号：US10189087
申请日：2002-07-03
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.
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