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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：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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3.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：US07497663B2
公开(公告)日：2009-03-03
申请号：US11586952
申请日：2006-10-26
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74 , Y10S416/02
摘要： An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only to four decimal places, wherein Y represents a distance from a platform on which the airfoil is mounted, and X and Z are coordinates defining the profile at each distance Y from the platform.
摘要翻译： 提供了一种用于转子叶片的翼型件，其包括基本上根据X，Y和Z的笛卡尔坐标值的未涂覆轮廓，以便于平衡转子叶片的性能和耐久性，并且有助于提高高压涡轮机的操作效率。 配置文件仅承载四位小数，其中Y表示与安装有翼型件的平台的距离，X和Z是从平台每个距离Y定义轮廓的坐标。
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公开(公告)号：US08500396B2
公开(公告)日：2013-08-06
申请号：US11507120
申请日：2006-08-21
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.
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公开(公告)号：US08425183B2
公开(公告)日：2013-04-23
申请号：US11602421
申请日：2006-11-20
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.
摘要翻译： 涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。 末端肋在翼型件的前缘和后缘之间间隔开，以包括限定三腔尖端腔的三尖头挡板。
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公开(公告)号：US09103213B2
公开(公告)日：2015-08-11
申请号：US13407905
申请日：2012-02-29
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F05D2240/80 , F05D2250/20 , Y02T50/673
摘要： A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.
摘要翻译： 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。 每个平台具有扇形流动表面，包括在平台的混合区域中切向开始的净化槽。 清洗槽轴向延伸到翼型的吸入侧，前缘的后部，以引导吹扫流。
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公开(公告)号：US08459956B2
公开(公告)日：2013-06-11
申请号：US12344058
申请日：2008-12-24
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80 , F05D2270/17 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
摘要翻译： 涡轮机叶片包括在其根部处的翼型件和整体式平台。 该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。
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公开(公告)号：US07686578B2
公开(公告)日：2010-03-30
申请号：US11507121
申请日：2006-08-21
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.
摘要翻译： 涡轮机叶片包括具有从尖端底板延伸的第一和第二末端肋的翼面末端。 肋沿刀片的相对的压力和吸力侧延伸并且在相对的前缘和后缘连接在一起。 尖端挡板横向嵌套在肋之间，并且与第二肋条一致，以使翼型件尖端分叉成沿相应的压力侧和吸力侧延伸的第一和第二尖端口袋。
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公开(公告)号：US06786696B2
公开(公告)日：2004-09-07
申请号：US10139534
申请日：2002-05-06
IPC分类号： F01D530
CPC分类号： F01D5/3007 , F01D5/147 , Y02E10/721 , Y02T50/671 , Y02T50/673
摘要： A turbine blade includes an airfoil and dovetail. The dovetail includes a pair of supporting tangs. A rectangular root block bridges the tangs over a majority of the root end thereof. The block terminates short of one endface of the dovetail to form a root notch thereat for preferentially reducing weight.
摘要翻译： 涡轮叶片包括翼型件和燕尾形件。 燕尾包括一对支撑柄。 矩形根块在其根部的大部分端部上桥接桥脚。 该块终止于燕尾榫的一个端面，以在其上形成根切口，以优先减轻重量。
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