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公开(公告)号：US20130136592A1
公开(公告)日：2013-05-30
申请号：US13304720
申请日：2011-11-28
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D1/04 , F01D5/142 , F05D2250/74
摘要： A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle 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.
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公开(公告)号：US08827641B2
公开(公告)日：2014-09-09
申请号：US13304720
申请日：2011-11-28
CPC分类号： F01D9/02 , F01D1/04 , F01D5/142 , F05D2250/74
摘要： A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle 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： 提供了一种涡轮喷嘴，其包括具有翼型形状的喷嘴翼型，喷嘴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：US20130104550A1
公开(公告)日：2013-05-02
申请号：US13284068
申请日：2011-10-28
CPC分类号： F01D5/141 , F05D2240/125 , F05D2240/307
摘要： A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.
摘要翻译： 提供涡轮机的涡轮机并且包括限定用于流体流动的路径的相对的端壁以及沿着该路径轴向设置的多个交错的叶片级和喷嘴级。 多个叶片级在通路的下游端包括最后的叶片级，并且在最后叶片级的上游包括一个最后叶片级。 多个喷嘴级包括在最后的叶片级和下一个到最后的叶片级之间的最后一个喷嘴级，以及从下一个到最后的叶片级上游的最后一个喷嘴级。 下一个到最后的叶片级和下一个到最后的喷嘴级中的至少一个包括配置成与流体流相互作用并且限定喉部分布的气动元件，其产生流体流中的尖端强压力分布。
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公开(公告)号：US09255480B2
公开(公告)日：2016-02-09
申请号：US13284068
申请日：2011-10-28
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/125 , F05D2240/307
摘要： A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.
摘要翻译： 提供涡轮机的涡轮机并且包括限定用于流体流动的路径的相对的端壁以及沿着该路径轴向设置的多个交错的叶片级和喷嘴级。 多个叶片级在通路的下游端包括最后的叶片级，并且在最后叶片级的上游包括一个最后叶片级。 多个喷嘴级包括在最后的叶片级和下一个到最后的叶片级之间的最后一个喷嘴级，以及从下一个到最后的叶片级上游的最后一个喷嘴级。 下一个到最后的叶片级和下一个到最后的喷嘴级中的至少一个包括配置成与流体流相互作用并且限定喉部分布的气动元件，其产生流体流中的尖端强压力分布。
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公开(公告)号：US20150345306A1
公开(公告)日：2015-12-03
申请号：US14824953
申请日：2015-08-12
申请人： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , Spencer Aaron Kareff
发明人： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , Spencer Aaron Kareff
CPC分类号： F01D5/225 , F01D5/141 , F01D5/20 , F01D11/02 , F05D2220/31 , F05D2220/32 , F05D2240/307 , F05D2250/20 , F05D2250/73 , Y02T50/671 , Y02T50/673
摘要： Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.
摘要翻译： 本公开的实施例涉及包括具有压力侧部分和吸力侧部分的涡轮机叶片梢罩的系统。 压力侧部分和吸力侧部分被涡轮机叶片的平均曲线划分，并且压力侧部分具有比吸力侧部分更大的表面积。
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公开(公告)号：US09500085B2
公开(公告)日：2016-11-22
申请号：US13555434
申请日：2012-07-23
CPC分类号： F01D5/142 , F05D2220/321 , F05D2220/3216 , Y02T50/673
摘要： A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.
摘要翻译： 一种用于增强具有至少一排时钟翼型的燃气轮机的一个或多个性能参数的方法通常可以包括选择第一排，第二排和第三排翼型件，其中第三排相对于第一排计时。 可以使用不稳定的计算流体动力学模型来确定从翼型的第二排流到翼型的第三排的工作流体的至少一个尾流参数。 可以修改第二排的翼型件的至少一个设计参数，然后可以使用不稳定的计算流体动力学模型来确定翼型设计参数修改对至少一个尾流参数的影响。 可以将对唤醒参数的影响与预定目标范围进行比较。
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公开(公告)号：US08845296B2
公开(公告)日：2014-09-30
申请号：US13235765
申请日：2011-09-19
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74 , Y10S416/02
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 Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, 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 profile sections at the 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件，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Z值是来自0的无量纲值 通过将Z值乘以翼型件的高度（英寸）并增加翼型件底座的半径，其中X和Y是以英寸为单位的距离，当通过平滑的连续弧连接时， 在每个距离Z处限定翼型轮廓部分，Z距离处的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：US08734116B2
公开(公告)日：2014-05-27
申请号：US13304725
申请日：2011-11-28
CPC分类号： F01D5/142 , 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.
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公开(公告)号：US20130189106A1
公开(公告)日：2013-07-25
申请号：US13355436
申请日：2012-01-20
申请人： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , Spencer Aaron Kareff
发明人： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , Spencer Aaron Kareff
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F01D5/141 , F01D5/20 , F01D11/02 , F05D2220/31 , F05D2220/32 , F05D2240/307 , F05D2250/20 , F05D2250/73 , Y02T50/671 , Y02T50/673
摘要： Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.
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公开(公告)号：US20140020395A1
公开(公告)日：2014-01-23
申请号：US13555434
申请日：2012-07-23
IPC分类号： F02C9/16
CPC分类号： F01D5/142 , F05D2220/321 , F05D2220/3216 , Y02T50/673
摘要： A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.
摘要翻译： 一种用于增强具有至少一排时钟翼型的燃气轮机的一个或多个性能参数的方法通常可以包括选择第一排，第二排和第三排翼型件，其中第三排相对于第一排计时。 可以使用不稳定的计算流体动力学模型来确定从翼型的第二排流到翼型的第三排的工作流体的至少一个尾流参数。 可以修改第二排的翼型件的至少一个设计参数，然后可以使用不稳定的计算流体动力学模型来确定翼型设计参数修改对至少一个尾流参数的影响。 可以将对唤醒参数的影响与预定目标范围进行比较。
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