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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: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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公开(公告)号:US06672829B1
公开(公告)日:2004-01-06
申请号:US10196623
申请日:2002-07-16
申请人: David Glenn Cherry , Ching-Pang Lee , Chander Prakash , Aspi Rustom Wadia , Brian David Keith , Steven Robert Brassfield
发明人: David Glenn Cherry , Ching-Pang Lee , Chander Prakash , Aspi Rustom Wadia , Brian David Keith , Steven Robert Brassfield
IPC分类号: F01D518
CPC分类号: F01D5/141 , F01D5/145 , F01D5/20 , F05D2250/292
摘要: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.
摘要翻译: 一种用于燃气涡轮发动机的涡轮机叶片,包括翼型件和整体式燕尾榫,用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括:在前缘和后缘处连接在一起的第一和第二侧壁,其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板,用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度,用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的,或者可以在其上变化。 因此,燃烧气体的再循环区域形成在尖端肋的远端附近,这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。
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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:US09085985B2
公开(公告)日:2015-07-21
申请号:US13429312
申请日:2012-03-23
IPC分类号: F01D5/14
CPC分类号: F01D5/143 , F01D5/141 , F01D5/145 , F05D2240/304 , F05D2250/611 , F05D2250/711 , F05D2250/712 , 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. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.
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。 至少一些平台具有扇形流动表面,其包括邻近压力侧的凸起和邻接相应翼型件的前缘的吸力侧的碗。 凸起构造成具有位于其相应流动通道内的最大高度,并且其中凸起在前后方向上的高度减小,并且朝向翼型的压力侧横向降低,并且朝向毗邻吸入侧的碗 下一个相邻的翼型。
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公开(公告)号:US20130251520A1
公开(公告)日:2013-09-26
申请号:US13429312
申请日:2012-03-23
CPC分类号: F01D5/143 , F01D5/141 , F01D5/145 , F05D2240/304 , F05D2250/611 , F05D2250/711 , F05D2250/712 , 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. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.
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。 至少一些平台具有扇形流动表面,其包括邻近压力侧的凸起和邻接相应翼型件的前缘的吸力侧的碗。 凸起构造成具有位于其相应流动通道内的最大高度,并且其中凸起在前后方向上的高度减小,并且朝向翼型的压力侧横向降低,并且朝向毗邻吸入侧的碗 下一个相邻的翼型。
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公开(公告)号:US08512003B2
公开(公告)日:2013-08-20
申请号:US11507116
申请日:2006-08-21
IPC分类号: F01D5/14
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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