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公开(公告)号：US20130108452A1
公开(公告)日：2013-05-02
申请号：US13284521
申请日：2011-10-28
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/20 , Y02T50/673
摘要： Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.
摘要翻译： 本公开的某些实施例包括具有涡轮机的系统，该涡轮机包括耦合到转子的多个涡轮机叶片，其中每个涡轮机叶片具有叶片基部和相对于叶片基部扩张的扩口叶片尖端部分。 另外，每个涡轮机叶片的后缘沿公共平面延伸。
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2.发明申请TURBINE AIRFOIL AND METHOD OF CONTROLLING A TEMPERATURE OF A TURBINE AIRFOIL 审中-公开涡轮机空气和控制涡轮机空气温度的方法公开(公告)号：US20130039758A1
公开(公告)日：2013-02-14
申请号：US13205763
申请日：2011-08-09
申请人： Aaron Ezekiel Smith , Bradley Taylor Boyer , Anthony Louis Giglio , Ross James Gustafson , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Bradley Taylor Boyer , Anthony Louis Giglio , Ross James Gustafson , Christopher Michael Penny
IPC分类号： F01D5/18
CPC分类号： F01D11/04 , F01D11/006 , F05D2240/81 , F05D2260/205 , F05D2260/2212 , F05D2260/22141
摘要： According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life.
摘要翻译： 根据本发明的一个方面，涡轮机翼片包括平台和从平台延伸的叶片。 翼型件还包括形成在平台的斜面中的槽，该槽被配置为经由通道接收加压流体并且构造成将加压流体引导到涡轮机翼型的选定区域以改善翼型件的寿命。
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公开(公告)号：US20130136611A1
公开(公告)日：2013-05-30
申请号：US13304743
申请日：2011-11-28
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74
摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译： 提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X，Y和Z的笛卡尔坐标值 是通过将X，Y和Z的笛卡尔坐标值乘以翼型的高度（英寸），其中X和Y是以英寸为单位的距离，其中，当 通过平滑连续的弧连接，在每个距离Z处限定翼型轮廓部分，Z距离处的翼型轮廓部分彼此平滑地连接以形成完整的翼型形状。
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公开(公告)号：US09051842B2
公开(公告)日：2015-06-09
申请号：US13344530
申请日：2012-01-05
CPC分类号： F01D5/187 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2240/304 , F05D2250/131 , F05D2250/323 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.
摘要翻译： 一种系统包括涡轮机叶片，其包括至少一个冷却槽，该冷却槽构造成沿涡轮叶片的内部到外部在流动方向上输送冷却剂。 冷却槽包括连接到内部的入口和入口下游的会聚部分。 会聚部分包括在流动方向上减小的第一横截面面积。 冷却槽还包括沿涡轮叶片的后缘设置的出口。
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公开(公告)号：US20130209253A1
公开(公告)日：2013-08-15
申请号：US13370949
申请日：2012-02-10
CPC分类号： F01D5/3007 , F01D5/26
摘要： According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.
摘要翻译： 根据本发明的一个方面，涡轮组件包括从叶片延伸的翼型件和位于叶片下部的燕尾榫，其中燕尾榫具有燕尾接触表面。 涡轮机组件还包括具有狭槽的构件，槽被配置成经由燕尾形件连接到翼型件，该槽具有接触燕尾接触表面的槽接触表面，其中燕尾接触表面被减压以改变基部频率 叶片和构件的组件。
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公开(公告)号：US20130177446A1
公开(公告)日：2013-07-11
申请号：US13344530
申请日：2012-01-05
CPC分类号： F01D5/187 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2240/304 , F05D2250/131 , F05D2250/323 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.
摘要翻译： 一种系统包括涡轮机叶片，其包括至少一个冷却槽，该冷却槽构造成沿涡轮叶片的内部到外部在流动方向上输送冷却剂。 冷却槽包括连接到内部的入口和入口下游的会聚部分。 会聚部分包括在流动方向上减小的第一横截面面积。 冷却槽还包括沿涡轮叶片的后缘设置的出口。
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公开(公告)号：US09151167B2
公开(公告)日：2015-10-06
申请号：US13370949
申请日：2012-02-10
CPC分类号： F01D5/3007 , F01D5/26
摘要： According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.
摘要翻译： 根据本发明的一个方面，涡轮组件包括从叶片延伸的翼型件和位于叶片下部的燕尾榫，其中燕尾榫具有燕尾接触表面。 涡轮机组件还包括具有狭槽的构件，槽被配置成经由燕尾形件连接到翼型件，该槽具有接触燕尾接触表面的槽接触表面，其中燕尾接触表面被减压以改变基部频率 叶片和构件的组件。
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公开(公告)号：US08894376B2
公开(公告)日：2014-11-25
申请号：US13284521
申请日：2011-10-28
CPC分类号： F01D5/141 , F01D5/20 , Y02T50/673
摘要： Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.
摘要翻译： 本公开的某些实施例包括具有涡轮机的系统，该涡轮机包括耦合到转子的多个涡轮机叶片，其中每个涡轮机叶片具有叶片基部和相对于叶片基部扩张的扩口叶片尖端部分。 另外，每个涡轮机叶片的后缘沿公共平面延伸。
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公开(公告)号：US20130115096A1
公开(公告)日：2013-05-09
申请号：US13288100
申请日：2011-11-03
IPC分类号： F01D5/14
CPC分类号： F01D11/02 , F01D5/288 , Y02T50/671
摘要： A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.
摘要翻译： 装备有一个或多个天使翼的旋转翼型零件，其阻止热工作流体进入其中安装该部件的涡轮机的内部区域。 该部件包括翼型件和用于安装部件以使部件在涡轮机内旋转的特征。 天使翼从部件突出以具有面向翼型的第一表面，面对安装特征的相对设置的第二表面以及其间的至少一个侧表面。 绝热涂层系统存在于第一表面上以抑制从工作流体传递到天使翼而不是在第二或侧面上的热传递，从而不会妨碍从天使翼的第二和侧面的热传递。
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公开(公告)号：US09011101B2
公开(公告)日：2015-04-21
申请号：US13304743
申请日：2011-11-28
申请人： Ross James Gustafson , Christopher Michael Penny , Aaron Ezekiel Smith , Luke C Sponsellar , William Scott Zemitis
发明人： Ross James Gustafson , Christopher Michael Penny , Aaron Ezekiel Smith , Luke C Sponsellar , William Scott Zemitis
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74
摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译： 提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X，Y和Z的笛卡尔坐标值 是通过将X，Y和Z的笛卡尔坐标值乘以翼型的高度（英寸），其中X和Y是以英寸为单位的距离，其中，当 通过平滑连续的弧连接，在每个距离Z处限定翼型轮廓部分，Z距离处的翼型轮廓部分彼此平滑地连接以形成完整的翼型形状。
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