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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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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：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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Patent Agency Ranking
6.发明申请公开(公告)号：US20220341332A1
公开(公告)日：2022-10-27
申请号：US17691377
申请日：2022-03-10
Applicant: General Electric Company
Abstract: A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.
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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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8.发明公开公开(公告)号：US20240159154A1
公开(公告)日：2024-05-16
申请号：US18379433
申请日：2023-10-12
Applicant: General Electric Company
CPC classification number: F01D5/225 , F01D5/005 , F01D5/141 , F01D5/143 , F05D2220/30 , F05D2220/3213 , F05D2230/80 , F05D2240/30 , F05D2250/74
Abstract: A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.
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9.发明授权公开(公告)号：US11821336B2
公开(公告)日：2023-11-21
申请号：US17691377
申请日：2022-03-10
Applicant: General Electric Company
CPC classification number: F01D5/225 , F01D5/005 , F01D5/141 , F01D5/143 , F05D2220/30 , F05D2220/3213 , F05D2230/80 , F05D2240/30 , F05D2250/74
Abstract: A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.
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公开(公告)号：US10436034B2
公开(公告)日：2019-10-08
申请号：US15594704
申请日：2017-05-15
Applicant: General Electric Company
Inventor： Lee Larned Brozyna , Mark Andrew Jones , Matthew Lutz , Srinivasa Govardhan Jayana
IPC: F01D5/14
Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I 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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