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公开(公告)号：US08876485B2
公开(公告)日：2014-11-04
申请号：US13304730
申请日：2011-11-28
CPC分类号： F01D5/141 , F01D9/041 , F05D2240/12 , F05D2240/30 , F05D2250/74
摘要： The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. 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. The X and Y values 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 may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US20130136589A1
公开(公告)日：2013-05-30
申请号：US13304730
申请日：2011-11-28
CPC分类号： F01D5/141 , F01D9/041 , F05D2240/12 , F05D2240/30 , F05D2250/74
摘要： The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. 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. The X and Y values 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 may be joined smoothly with one another to form a complete airfoil shape.
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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：US20110271689A1
公开(公告)日：2011-11-10
申请号：US12775401
申请日：2010-05-06
申请人： Benjamin Paul Lacy , Ashok Kumar Anand , Raymond Edward Chupp , Andres Jose Garcia-Crespo , Ross James Gustafson
发明人： Benjamin Paul Lacy , Ashok Kumar Anand , Raymond Edward Chupp , Andres Jose Garcia-Crespo , Ross James Gustafson
IPC分类号： F02C7/18
CPC分类号： F01D9/023 , F01D25/12 , F01D25/14 , F05D2260/213 , Y02T50/676
摘要： In one embodiment, a compressor discharge casing of a gas turbine engine is designed to receive discharge air from a compressor and to direct a first portion of the discharge air into a combustor of the gas turbine engine and a second portion of the discharge air into a nozzle assembly of a gas turbine to cool components of the gas turbine. A heat transfer device is configured to receive a cooling fluid and to cool the second portion of the discharge air with the cooling fluid.
摘要翻译： 在一个实施例中，燃气涡轮发动机的压缩机排放壳体被设计成从压缩机接收排出空气并且将排出空气的第一部分引导到燃气涡轮发动机的燃烧器中，并且将排出空气的第二部分引导到 燃气轮机的喷嘴组件以冷却燃气轮机的部件。 传热装置构造成接收冷却流体并用冷却流体冷却排出空气的第二部分。
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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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6.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：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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公开(公告)号：US08998577B2
公开(公告)日：2015-04-07
申请号：US13288057
申请日：2011-11-03
CPC分类号： F01D9/041 , F01D5/142 , F05D2220/3215
摘要： The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.
摘要翻译： 因此，本申请提供了一种燃气轮机。 燃气涡轮发动机可以包括位于涡轮机下游的涡轮机和扩散器。 涡轮可以包括多个最后阶段的桶，多个最后阶段的喷嘴，以及最后阶段喷嘴的测量比为大约0.95或更大。
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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：US20130115075A1
公开(公告)日：2013-05-09
申请号：US13288057
申请日：2011-11-03
CPC分类号： F01D9/041 , F01D5/142 , F05D2220/3215
摘要： The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.
摘要翻译： 因此，本申请提供了一种燃气轮机。 燃气涡轮发动机可以包括位于涡轮机下游的涡轮机和扩散器。 涡轮可以包括多个最后阶段的桶，多个最后阶段的喷嘴，以及最后阶段喷嘴的测量比为大约0.95或更大。
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