专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US09011101B2 Turbine bucket airfoil profile 有权
标题翻译：涡轮斗翼型材
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。

2. 发明申请

US20130039758A1 TURBINE AIRFOIL AND METHOD OF CONTROLLING A TEMPERATURE OF A TURBINE AIRFOIL 审中-公开
标题翻译：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。

3. 发明申请

US20130136611A1 TURBINE BUCKET AIRFOIL PROFILE 有权
标题翻译：涡轮机底盘气翼型材
公开(公告)号：US20130136611A1
公开(公告)日：2013-05-30
申请号：US13304743
申请日：2011-11-28
申请人： Ross James Gustafson , Christopher Michael Penny , Aaron Ezekiel Smith , Luke C. Sponseller
发明人： Ross James Gustafson , Christopher Michael Penny , Aaron Ezekiel Smith , Luke C. Sponseller
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。

4. 发明授权

US09051842B2 System and method for cooling turbine blades 有权
标题翻译：冷却涡轮叶片的系统和方法
公开(公告)号：US09051842B2
公开(公告)日：2015-06-09
申请号：US13344530
申请日：2012-01-05
申请人： Aaron Ezekiel Smith , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Christopher Michael Penny
IPC分类号： F01D5/18 , F01D25/12
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。

5. 发明申请

US20130177446A1 SYSTEM AND METHOD FOR COOLING TURBINE BLADES 有权
标题翻译：用于冷却涡轮叶片的系统和方法
公开(公告)号：US20130177446A1
公开(公告)日：2013-07-11
申请号：US13344530
申请日：2012-01-05
申请人： Aaron Ezekiel Smith , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Christopher Michael Penny
IPC分类号： F01D5/18 , B22C9/10 , B22D25/02
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。

6. 发明申请

US20130115096A1 ROTATING AIRFOIL COMPONENT OF A TURBOMACHINE 有权
标题翻译：旋转涡轮机组的旋风分量
公开(公告)号：US20130115096A1
公开(公告)日：2013-05-09
申请号：US13288100
申请日：2011-11-03
申请人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
发明人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
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。

7. 发明授权

US08967957B2 Rotating airfoil component of a turbomachine 有权
标题翻译：涡轮机的旋翼型部件
公开(公告)号：US08967957B2
公开(公告)日：2015-03-03
申请号：US13288100
申请日：2011-11-03
申请人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
发明人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
IPC分类号： F04D29/08 , F01D11/02 , F01D5/28
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。

8. 发明授权

US09447691B2 Bucket assembly treating apparatus and method for treating bucket assembly 有权
标题翻译：铲斗总成处理装置及方法
公开(公告)号：US09447691B2
公开(公告)日：2016-09-20
申请号：US13214583
申请日：2011-08-22
申请人： Aaron Ezekiel Smith , Gary Michael Itzel , Scott Edmond Ellis
发明人： Aaron Ezekiel Smith , Gary Michael Itzel , Scott Edmond Ellis
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81
摘要： A bucket assembly and a method for treating a bucket assembly are disclosed. The bucket assembly includes a platform, the platform defining a platform cooling circuit, and an airfoil extending generally radially outward from the platform, the airfoil defining an airfoil cooling circuit. The bucket assembly additionally includes a lower body portion extending generally radially inward from the platform, the lower body portion defining a root and a cooling passage extending from the root, the cooling passage in fluid communication with the airfoil cooling circuit. The bucket assembly further includes a transfer passage defined between and in fluid communication with the airfoil cooling circuit and the platform cooling circuit such that a cooling medium may flow from the airfoil cooling circuit through the transfer passage to the platform cooling circuit.
摘要翻译：公开了一种用于处理铲斗组件的铲斗组件和方法。铲斗组件包括平台，限定平台冷却回路的平台和从平台大致径向向外延伸的翼型件，翼型件限定翼型冷却回路。铲斗组件还包括从平台大致径向向内延伸的下主体部分，下主体部分限定根部和从根部延伸的冷却通道，冷却通道与翼型件冷却回路流体连通。铲斗组件还包括一个传导通道，其限定在翼型件冷却回路和平台冷却回路之间并与其流体连通，使得冷却介质可以从翼型冷却回路通过传送通道流到平台冷却回路。

9. 发明授权

US09109454B2 Turbine bucket with pressure side cooling 有权
标题翻译：涡轮桶与压力侧冷却
公开(公告)号：US09109454B2
公开(公告)日：2015-08-18
申请号：US13409341
申请日：2012-03-01
申请人： Scott Edmond Ellis , Randall Richard Good , Bradley Taylor Boyer , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Randall Richard Good , Bradley Taylor Boyer , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2250/185
摘要： A turbine bucket for use with a gas turbine engine, as described herein, may include a platform, an airfoil extending from the platform, and a number of cooling circuits extending through the platform and the airfoil. One of the cooling circuits may be a serpentine cooling channel positioned within the platform.
摘要翻译：如本文所述，用于燃气涡轮发动机的涡轮机桶可以包括平台，从平台延伸的翼型件以及延伸穿过平台和翼型件的多个冷却回路。冷却回路中的一个可以是位于平台内的蛇形冷却通道。

10. 发明申请

US20130052036A1 PIN-FIN ARRAY 审中-公开
标题翻译： PIN-FIN阵列
公开(公告)号：US20130052036A1
公开(公告)日：2013-02-28
申请号：US13221009
申请日：2011-08-30
申请人： Aaron Ezekiel Smith
发明人： Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2240/304 , F05D2260/2212 , F05D2260/2214
摘要： The present application provides an airfoil with a cooling flow therein. The airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage. The pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.
摘要翻译：本申请提供其中具有冷却流的翼型件。翼型件可以包括内部冷却通道，与内部冷却通道连通的多个冷却孔以及位于内部冷却通道内的多个销翅片。销翅片布置有一个或多个转动开口和一个或多个引导开口，以便将冷却流引向冷却孔。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式