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1. 发明授权

US09039375B2 Non-axisymmetric airfoil platform shaping 有权
标题翻译：非轴对称翼型平台成型
公开(公告)号：US09039375B2
公开(公告)日：2015-05-26
申请号：US12551741
申请日：2009-09-01
申请人： Andrew Ray Kneeland , Andres Jose Garcia-Crespo , Bradley T. Boyer , Thomas William Vandeputte , Sylvain Pierre
发明人： Andrew Ray Kneeland , Andres Jose Garcia-Crespo , Bradley T. Boyer , Thomas William Vandeputte , Sylvain Pierre
IPC分类号： F01D5/14 , F01D11/02
CPC分类号： F01D5/141 , F01D5/142 , F01D5/143 , F01D11/02
摘要： Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.
摘要翻译：涡轮机的涡轮叶片组件包括安装在基座上的翼型件。基部的前缘和/或后缘设有弯曲部分。类似地，弯曲部分可以设置在涡轮叶片组件的角翼的前缘和/或后缘。此外，弯曲部分可以设置在涡轮机的喷嘴组件的前缘和/或后缘。

2. 发明申请

US20110052387A1 NON-AXISYMMETRIC AIRFOIL PLATFORM SHAPING 有权
标题翻译：非轴对称气翼平台形状
公开(公告)号：US20110052387A1
公开(公告)日：2011-03-03
申请号：US12551741
申请日：2009-09-01
申请人： Andrew Ray Kneeland , Andres Jose Garcia-Crespo , Bradley T. Boyer , Thomas William Vandeputte , Sylvain Pierre
发明人： Andrew Ray Kneeland , Andres Jose Garcia-Crespo , Bradley T. Boyer , Thomas William Vandeputte , Sylvain Pierre
IPC分类号： F01D9/02 , F01D5/14
CPC分类号： F01D5/141 , F01D5/142 , F01D5/143 , F01D11/02
摘要： Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.
摘要翻译：涡轮机的涡轮叶片组件包括安装在基座上的翼型件。基部的前缘和/或后缘设有弯曲部分。类似地，弯曲部分可以设置在涡轮叶片组件的角翼的前缘和/或后缘。此外，弯曲部分可以设置在涡轮机的喷嘴组件的前缘和/或后缘。

3. 发明授权

US09255480B2 Turbine of a turbomachine 有权
标题翻译：涡轮机的涡轮机
公开(公告)号：US09255480B2
公开(公告)日：2016-02-09
申请号：US13284068
申请日：2011-10-28
申请人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
发明人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
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。

4. 发明申请

US20130104550A1 TURBINE OF A TURBOMACHINE 有权
标题翻译：涡轮机的涡轮机
公开(公告)号：US20130104550A1
公开(公告)日：2013-05-02
申请号：US13284068
申请日：2011-10-28
申请人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
发明人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
IPC分类号： F02C3/04 , F01D1/00 , F01D1/04
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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