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公开(公告)号：US20130209258A1
公开(公告)日：2013-08-15
申请号：US13397296
申请日：2012-02-15
IPC分类号： F01D5/20
CPC分类号： F01D5/225 , F05D2250/314
摘要： A tip shrouded blade includes an airfoil rotatable about an axial centerline. Also included is a tip shroud connected at a radially outer tip of the airfoil, wherein the tip shroud includes at least one portion angled about a tangential axis defined by the radially outer tip of the airfoil.
摘要翻译： 尖端覆盖的叶片包括可围绕轴向中心线旋转的翼型件。 还包括连接在翼型件的径向外部末端处的尖端罩，其中尖端护罩包括围绕由翼型件的径向外部末端限定的切向轴线成角度的至少一个部分。
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公开(公告)号：US09097128B2
公开(公告)日：2015-08-04
申请号：US13407099
申请日：2012-02-28
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D5/3015 , F01D11/02 , F05D2250/38 , F05D2250/712 , F05D2300/175
摘要： A seal for a turbine engine is provided that includes a seal body disposed at a base of a turbine engine blade and a wing portion extending axially from the seal body. The wing portion has a first portion substantially parallel with a centerline of the engine and an angled upturn portion. The first portion extends between the seal body and the angled upturn portion. An angle between the engine centerline and the angled upturn portion is between about 0 degrees and about 90 degrees.
摘要翻译： 提供了一种用于涡轮发动机的密封件，其包括设置在涡轮发动机叶片的基部处的密封体和从密封体轴向延伸的翼部。 翼部具有基本上平行于发动机的中心线的第一部分和倾斜的上翘部分。 第一部分在密封体和倾斜的上翘部分之间延伸。 发动机中心线和倾斜上翻部分之间的角度在约0度和约90度之间。
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公开(公告)号：US08591192B2
公开(公告)日：2013-11-26
申请号：US13488901
申请日：2012-06-05
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/3023 , F01D11/008 , F05D2240/80
摘要： Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine.
摘要翻译： 公开了一种用于涡轮机的转子组件，其包括具有第一轴向面和第二轴向面的盘。 圆盘包括围绕盘的外表面延伸的至少一个周向燕尾榫和从第一轴向面延伸到第二轴向面的多个轴向燕尾榫。 多个叶片的每个叶片安装在多个轴向燕尾的轴向燕尾榫中，并且多个平台的每个平台通过至少一个周向燕尾座与多个叶片的叶片相邻地安装。 还公开了一种用于涡轮机的转子的组装方法。
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公开(公告)号：US20120240399A1
公开(公告)日：2012-09-27
申请号：US13488901
申请日：2012-06-05
IPC分类号： B23P15/02
CPC分类号： F01D5/3007 , F01D5/3023 , F01D11/008 , F05D2240/80
摘要： Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine.
摘要翻译： 公开了一种用于涡轮机的转子组件，其包括具有第一轴向面和第二轴向面的盘。 圆盘包括围绕盘的外表面延伸的至少一个周向燕尾榫和从第一轴向面延伸到第二轴向面的多个轴向燕尾榫。 多个叶片的每个叶片安装在多个轴向燕尾的轴向燕尾榫中，并且多个平台的每个平台通过至少一个周向燕尾座与多个叶片的叶片相邻地安装。 还公开了一种用于涡轮机的转子的组装方法。
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公开(公告)号：US20100232938A1
公开(公告)日：2010-09-16
申请号：US12402800
申请日：2009-03-12
CPC分类号： F01D5/26 , F01D5/3015 , F01D11/006
摘要： A gas turbine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a coverplate that is fastened to the wheel and the bucket and a seal positioned between the coverplate and the wheel and the bucket.
摘要翻译： 一种用于机器的燃气轮机和密封组件，其具有旋转轴，联接到旋转轴的轮，所述轮包括联接到所述车轮的铲斗，所述铲斗包括紧固到所述车轮和所述铲斗的盖板和位于所述车轮之间的密封件 盖板和砂轮和铲斗。
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公开(公告)号：US09309782B2
公开(公告)日：2016-04-12
申请号：US13616129
申请日：2012-09-14
摘要： A damper system for the buckets of a gas turbine engine. The damper system may include damper pins having a generally rounded top portion and a generally flat bottom portion along substantially the entire length thereof. The generally flat bottom portion may allow addition or removal of material to or from the pin in order to achieve an optimal dynamic weight ratio.
摘要翻译： 一种用于燃气涡轮发动机的水桶的阻尼器系统。 阻尼器系统可以包括阻尼销，其具有大致圆形的顶部部分和大致平坦的底部部分，大体上在其整个长度上。 大体上平坦的底部部分可以允许将材料添加到销或从销移出，以获得最佳的动态重量比。
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公开(公告)号：US20140079529A1
公开(公告)日：2014-03-20
申请号：US13616129
申请日：2012-09-14
IPC分类号： F01D25/06
摘要： A damper system for the buckets of a gas turbine engine. The damper system may include damper pins having a generally rounded top portion and a generally flat bottom portion along substantially the entire length thereof. The generally flat bottom portion may allow addition or removal of material to or from the pin in order to achieve an optimal dynamic weight ratio.
摘要翻译： 一种用于燃气涡轮发动机的水桶的阻尼器系统。 阻尼器系统可以包括阻尼销，其具有大致圆形的顶部部分和大致平坦的底部部分，大体上在其整个长度上。 大体上平坦的底部部分可以允许将材料添加到销或从销移出，以获得最佳的动态重量比。
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公开(公告)号：US08277190B2
公开(公告)日：2012-10-02
申请号：US12412969
申请日：2009-03-27
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/3023 , F01D11/008 , F05D2240/80
摘要： Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine.
摘要翻译： 公开了一种用于涡轮机的转子组件，其包括具有第一轴向面和第二轴向面的盘。 圆盘包括围绕盘的外表面延伸的至少一个周向燕尾榫和从第一轴向面延伸到第二轴向面的多个轴向燕尾榫。 多个叶片的每个叶片安装在多个轴向燕尾的轴向燕尾榫中，并且多个平台的每个平台通过至少一个周向燕尾座与多个叶片的叶片相邻地安装。 还公开了一种用于涡轮机的转子的组装方法。
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公开(公告)号：US08727724B2
公开(公告)日：2014-05-20
申请号：US12758320
申请日：2010-04-12
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/085 , F05D2230/11 , F05D2260/22141
摘要： A turbine bucket is provided and includes a shank interconnectable with a rotor and formed to accommodate coolant therein and an airfoil blade coupled to a radially outward portion of the shank and including a body formed to define a substantially radially extending cooling hole therein, which is disposed to be solely receptive of the coolant accommodated within the shank for removing heat from the body, the cooling hole being further defined as having a substantially non-circular cross-sectional shape at a predefined radial position of the body.
摘要翻译： 涡轮机桶被设置并且包括可与转子互连并形成以容纳冷却剂的柄，以及联接到柄的径向向外部分的翼型叶片，并且包括形成为在其中限定基本上径向延伸的冷却孔的主体， 仅容纳容纳在柄内的冷却剂以便从身体移除热量，冷却孔被进一步限定为在身体的预定的径向位置处具有基本上非圆形的横截面形状。
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公开(公告)号：US20130224026A1
公开(公告)日：2013-08-29
申请号：US13407099
申请日：2012-02-28
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D5/3015 , F01D11/02 , F05D2250/38 , F05D2250/712 , F05D2300/175
摘要： In one aspect, a seal for a turbine engine includes a seal body disposed at a base of a turbine engine blade and a wing portion extending axially from said seal body. The wing portion has a first portion substantially parallel with a centerline of the engine and an angled upturn portion. The first portion extends between the seal body and the angled upturn portion. An angle between the engine centerline and the angled upturn portion is between about 0 degrees and about 90 degrees.
摘要翻译： 一方面，一种用于涡轮发动机的密封件包括设置在涡轮发动机叶片的基部处的密封体和从所述密封体轴向延伸的翼部。 翼部具有基本上平行于发动机的中心线的第一部分和倾斜的上翘部分。 第一部分在密封体和倾斜的上翘部分之间延伸。 发动机中心线和倾斜上翻部分之间的角度在约0度和约90度之间。
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