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公开(公告)号：US09322282B2
公开(公告)日：2016-04-26
申请号：US13690361
申请日：2012-11-30
Applicant: General Electric Company
Inventor： Rohit Chouhan , Harish Bommanakatte , Sumeet Soni , Srinivasa Govardhan Jayana , Spencer Aaron Kareff
CPC classification number: F01D5/225 , F01D5/143 , F05D2240/307 , F05D2250/74
Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.
Abstract translation: 提供涡轮转子叶片。 涡轮转子叶片包括翼型件，翼型件末端，尖端护罩和围绕翼型件末端和尖端护罩的相交处的圆角。 圆角定义了一个关于交点的圆角轮廓变量，作为交叉口空气动力学气流的函数。
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公开(公告)号：US20160076385A1
公开(公告)日：2016-03-17
申请号：US14949544
申请日：2015-11-23
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Spencer Aaron Kareff
CPC classification number: F01D5/225 , F01D5/143 , F01D11/02 , F04D29/164 , F05D2240/303 , F05D2240/307 , F05D2250/73 , Y02T50/671 , Y02T50/673
Abstract: 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：US10253638B2
公开(公告)日：2019-04-09
申请号：US14824953
申请日：2015-08-12
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , Spencer Aaron Kareff
Abstract: 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：US20150107266A1
公开(公告)日：2015-04-23
申请号：US14061146
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Ross James Gustafson , Srinivasa Govardhan Jayana , Spencer Aaron Kareff , Dipesh Dinesh Nanda
IPC: F01D5/02
CPC classification number: F01D5/02 , F01D5/141 , F05D2250/74 , Y02E20/16 , Y02T50/671 , Y02T50/673
Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.
Abstract translation: 可以使用可用于确定相邻翼型之间的喉部的特定翼型轮廓来提高涡轮机频率调节，流体动力学效率和性能。 通过根据特定轮廓对喉部进行成型，可以对端壁的总压力进行通电，提高涡轮的性能。
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公开(公告)号：US20140154079A1
公开(公告)日：2014-06-05
申请号：US13690361
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Rohit Chouhan , Harish Bommanakatte , Sumeet Soni , Srinivasa Govardhan Jayana , Spencer Aaron Kareff
IPC: F01D5/22
CPC classification number: F01D5/225 , F01D5/143 , F05D2240/307 , F05D2250/74
Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.
Abstract translation: 提供涡轮转子叶片。 涡轮转子叶片包括翼型件，翼型件末端，尖端护罩和围绕翼型件末端和尖端护罩的相交处的圆角。 圆角定义了一个关于交点的圆角轮廓变量，作为交叉点的空气动力学气流的函数。
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Patent Agency Ranking
公开(公告)号：US10138736B2
公开(公告)日：2018-11-27
申请号：US14949544
申请日：2015-11-23
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Spencer Aaron Kareff
Abstract: 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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7.发明授权公开(公告)号：US09464530B2
公开(公告)日：2016-10-11
申请号：US14185161
申请日：2014-02-20
Applicant: General Electric Company
Inventor： Spencer Aaron Kareff , Matthew Robert Piersall , Danielle Werner
CPC classification number: F01D5/30 , F01D5/20 , F01D5/225 , Y02T50/671
Abstract: The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine.
Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮机桶。 涡轮机桶可以包括翼型，从翼型件径向向外定位的尖端护罩，以及从尖端护罩径向向外定位并沿大致切线方向从尖端护罩的第一端延伸到第二端的密封轨道。 密封导轨可以在位于第一端和第二端之间的位置处包括最大轴向厚度，并且在大致切线方向上偏离翼型。 本申请和所得到的专利进一步提供了一种燃气涡轮发动机和用于平衡燃气涡轮发动机的涡轮机叶片的尖端护罩的方法。
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公开(公告)号：US09347320B2
公开(公告)日：2016-05-24
申请号：US14061146
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Ross James Gustafson , Srinivasa Govardhan Jayana , Spencer Aaron Kareff , Dipesh Dinesh Nanda
CPC classification number: F01D5/02 , F01D5/141 , F05D2250/74 , Y02E20/16 , Y02T50/671 , Y02T50/673
Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.
Abstract translation: 可以使用可用于确定相邻翼型之间的喉部的特定翼型轮廓来提高涡轮机频率调节，流体动力学效率和性能。 通过根据特定轮廓对喉部进行成型，可以对端壁的总压力进行通电，提高涡轮的性能。
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公开(公告)号：US20160024930A1
公开(公告)日：2016-01-28
申请号：US14340059
申请日：2014-07-24
Applicant: General Electric Company
Inventor： Kelvin Rono Aaron , Craig Allen Bielek , Ross James Gustafson , Ariel Caesar Prepena Jacala , Spencer Aaron Kareff , Matthew Robert Piersall , John Franklin Ryman
IPC: F01D5/14
CPC classification number: F01D5/16 , F01D5/141 , F05D2240/305 , F05D2250/711 , F05D2260/941 , Y02T50/673
Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.
Abstract translation: 涡轮机翼型包括基部和从基部延伸到限定径向跨度尺寸的尖端部的叶片部分。 叶片部分包括前缘，后缘，压力侧和吸力侧。 在前缘和后缘之间限定轴向弦的尺寸。 在压力侧设置至少一个凸起。 至少一个突起从轴向弦尺寸的约10％延伸到轴向弦尺寸的约90％。
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10.发明申请公开(公告)号：US20150233258A1
公开(公告)日：2015-08-20
申请号：US14185161
申请日：2014-02-20
Applicant: General Electric Company
Inventor： Spencer Aaron Kareff , Matthew Robert Piersall , Danielle Werner
IPC: F01D5/30
CPC classification number: F01D5/30 , F01D5/20 , F01D5/225 , Y02T50/671
Abstract: The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine.
Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮机桶。 涡轮机桶可以包括翼型，从翼型件径向向外定位的尖端护罩，以及从尖端护罩径向向外定位并沿大致切线方向从尖端护罩的第一端延伸到第二端的密封轨道。 密封导轨可以在位于第一端和第二端之间的位置处包括最大轴向厚度，并且在大致切线方向上偏离翼型。 本申请和所得到的专利进一步提供了一种燃气涡轮发动机和用于平衡燃气涡轮发动机的涡轮机叶片的尖端护罩的方法。
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