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公开(公告)号：US20080145216A1
公开(公告)日：2008-06-19
申请号：US11642001
申请日：2006-12-19
CPC分类号： F01D11/001 , F01D5/143 , F01D11/04 , Y02T50/673
摘要： A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.
摘要翻译： 涡轮级包括具有安装在内带和外带之间的一排叶片的定子喷嘴。 内带终止于从叶片向后收敛的卵形突出部，其中凸起的顶部与径向外部和内部凸起表面接合。 卵形凸缘在一系列以下的涡轮转子叶片上减小了在旋转密封处的空气动力学损失。
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公开(公告)号：US07578653B2
公开(公告)日：2009-08-25
申请号：US11642001
申请日：2006-12-19
CPC分类号： F01D11/001 , F01D5/143 , F01D11/04 , Y02T50/673
摘要： A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.
摘要翻译： 涡轮级包括具有安装在内带和外带之间的一排叶片的定子喷嘴。 内带终止于从叶片向后收敛的卵形突出部，其中凸起的顶部与径向外部和内部凸起表面接合。 卵形凸缘在一系列以下的涡轮转子叶片上减小了在旋转密封处的空气动力学损失。
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公开(公告)号：US20080145208A1
公开(公告)日：2008-06-19
申请号：US11642002
申请日：2006-12-19
CPC分类号： F01D5/145 , F01D5/082 , F01D5/143 , F01D9/041 , F01D11/001 , F05D2250/19 , Y02T50/673 , Y02T50/676
摘要： A turbine stage includes a stator nozzle cooperating with a row of turbine blades. The nozzle includes a row of vanes mounted between inner and outer bands, with the inner band adjoining the blades at inner platforms thereof at a rotary seal. The inner band includes a stator bullnose at the trailing edge thereof cooperating with the rotary seal for reducing aerodynamic losses thereat.
摘要翻译： 涡轮级包括与一排涡轮叶片配合的定子喷嘴。 喷嘴包括安装在内带和外带之间的一排叶片，内带在其内平台处以旋转密封件邻接叶片。 内带在其后缘包括一个与旋转密封件配合的定子公牛，以减少其中的空气动力学损失。
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公开(公告)号：US20090324422A1
公开(公告)日：2009-12-31
申请号：US11507120
申请日：2006-08-21
IPC分类号： F01D5/18
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.
摘要翻译： 涡轮叶片包括具有沿相对的压力和吸力侧延伸的第一和第二肋的翼型端。 肋从尖端底部向外延伸并且在相对的前缘和后缘处连接在一起。 级联顶端挡板将尖端底部上方的两个肋横向地桥接在尖端的最大宽度的前方，以将端部弦状地分隔成挡板相对侧上的相应的尖端口。
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公开(公告)号：US08632311B2
公开(公告)日：2014-01-21
申请号：US11507119
申请日：2006-08-21
IPC分类号： F01D5/14
CPC分类号： F01D5/20 , F05D2250/712 , Y02T50/673
摘要： A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.
摘要翻译： 涡轮叶片包括终止在尖端中的翼型件。 尖端包括符合翼型件的凹入压力侧的第一肋条和与翼型件的凸形吸入侧相一致的第二肋条。 第二肋从吸力侧向外张开。
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公开(公告)号：US20080044291A1
公开(公告)日：2008-02-21
申请号：US11507132
申请日：2006-08-21
IPC分类号： B64C11/16
CPC分类号： F01D5/20 , F01D5/145 , F05D2250/70 , Y02T50/671 , Y02T50/673
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 tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.
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。末端肋在翼型的前缘和后缘之间间隔开，以包括顶端挡板。 所述挡板以第一肋条与第一肋条相反地延伸，以相反轮廓延伸，以限定第一凹槽，并且与第二肋条对置形成第二凹槽。
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公开(公告)号：US20080044290A1
公开(公告)日：2008-02-21
申请号：US11507121
申请日：2006-08-21
IPC分类号： B64C11/16
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：US20080044289A1
公开(公告)日：2008-02-21
申请号：US11507116
申请日：2006-08-21
IPC分类号： B64C11/16
CPC分类号： F01D5/20 , F05D2240/307 , F05D2250/292 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/20 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.
摘要翻译： 涡轮叶片包括从尖端底板延伸以限定尖端腔的第一和第二尖端肋。 出口斜坡桥接肋骨，并从地板上抬高。
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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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