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公开(公告)号：US11519273B1
公开(公告)日：2022-12-06
申请号：US17305908
申请日：2021-07-16
Applicant: General Electric Company
Inventor： Michael James Healy , Matthew John McKeever , Sabarinath Devarajan , Uday Krishna Pappala , Kevin Michael Barnett , Kumaran Vale Mudaliar , Wilfried Rick , Moorthi Subramaniyan , Karan Ghule , Denis Stankovic , Yu Wang , Marco Micheli , Mariadas Anton Charles Anandarajah , Michael Loetzerich
Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US11459892B1
公开(公告)日：2022-10-04
申请号：US17454162
申请日：2021-11-09
Applicant: General Electric Company
Inventor： Matthew John McKeever , Michael James Healy , Wilfried Rick , Rozila Nausheen , Sabarinath Devarajan , Moorthi Subramaniyan , Vsevolod Yuriyevich Ostrovskiy , Kumaran Vale Mudaliar , Damir Novak , Thomas Sommer , Aditya Rajeshbhai Shah , Uday Krishna Pappala , Kevin Michael Barnett , Josip Galic , Gurulakshmi Polisetty , Paul G. Deivernois , Dejan Mikasinovic
Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape having has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US20190264569A1
公开(公告)日：2019-08-29
申请号：US15903192
申请日：2018-02-23
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Adam John Fredmonski
Abstract: A turbine blade including an airfoil extending radially from a platform above a shank is disclosed. The airfoil has a leading edge; a trailing edge; and a pressure side wall and a suction side wall extending between the leading edge and trailing edge. The turbine blade includes a chamber in at least one of the airfoil and platform. The chamber is configured to deliver a first fluid therein having a higher pressure than a second fluid in a wheel space adjacent the shank. The turbine blade includes an exiting hole in fluid communication with the chamber, positioned at a location upstream of the leading edge and circumferentially to a side of a selected side wall of the pressure side wall and suction side wall. In operation, the first fluid exits the exiting hole to increase a momentum of a boundary layer film near the selected side wall, preventing wheel space leakage from negatively impacting the boundary layer film.
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公开(公告)号：US10288086B2
公开(公告)日：2019-05-14
申请号：US15285258
申请日：2016-10-04
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , John David Dyer
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180298760A1
公开(公告)日：2018-10-18
申请号：US15927153
申请日：2018-03-21
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Adam John Fredmonski , Francesco Soranna
Abstract: Stator vanes including curved trailing edges are disclosed. The stator vanes may include a body including a central section, a tip section positioned radially above the central section, and a root section positioned radially below the central section. The body of the stator vanes may also include a leading edge extending radially adjacent the root section, central section, and tip section, respectively, and a trailing edge positioned opposite and aft to the leading edge. The trailing edge may include a concave contour including a first portion radially aligned with the central section of the body. The first portion may be axially offset and forward of a reference line that may be perpendicular to an axial direction and intersects the concave contour at the tip section and the root section. A concavity of the first portion of the concave contour may be formed radially aft of the central section.
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Patent Agency Ranking
公开(公告)号：US09957964B2
公开(公告)日：2018-05-01
申请号：US14845388
申请日：2015-09-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Moorthi Subramaniyan , Jaya Rao Venkata Satya Vuppala
CPC classification number: F04D19/002 , F01D17/162 , F04D29/324 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2240/12 , F05D2250/20
Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
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公开(公告)号：US09631542B2
公开(公告)日：2017-04-25
申请号：US14301979
申请日：2014-06-11
Inventor： Moorthi Subramaniyan , Christian Michael Hansen , Richard A. Huntington , Todd Franklin Denman
CPC classification number: F01N13/08 , F01D25/30 , F02C3/34 , F02K1/40 , F02K1/48 , F05D2250/184 , F05D2250/611 , Y02E20/16
Abstract: A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products and a turbine section having one or more turbine stages between an upstream end and a downstream end. The one or more turbine stages are driven by the combustion products. The gas turbine engine also includes an exhaust section disposed downstream from the downstream end of the turbine section. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The gas turbine engine also includes a mixing device disposed in the exhaust section. The mixing device is configured to divide the exhaust gas into a first exhaust gas and a second exhaust gas, and to combine the first and second exhaust gases in a mixing region to produce a mixed exhaust gas.
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公开(公告)号：US09453417B2
公开(公告)日：2016-09-27
申请号：US13633651
申请日：2012-10-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Prabakaran Modachur Krishnan , Kevin Joseph Barb , Srikanth Deshpande , Moorthi Subramaniyan
CPC classification number: F01D9/041 , F01D5/143 , F01D5/145 , F01D9/04 , F01D11/08 , F05D2240/125 , F05D2240/126 , Y02E20/16
Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.
Abstract translation: 公开了通过将泄漏流动的方向与涡轮主流的流路重新导向和/或对准来减少涡轮机中的风阻和混合损失的系统和装置。 在一个实施例中，一种装置包括：基座，其构造成连接到涡轮的隔膜; 以及径向部分，其连接到所述基部并且从所述基部朝向所述涡轮机的转子径向向内延伸，所述径向部分被定向成以与主工作流体互补的角度径向地调节工作流体的泄漏流的行进方向 涡轮机路径。
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公开(公告)号：US09394797B2
公开(公告)日：2016-07-19
申请号：US13693610
申请日：2012-12-04
Applicant: General Electric Company
Inventor： Debabrata Mukhopadhyay , Steven Sebastian Burdgick , Prashant Prabhakar Sankolli , Moorthi Subramaniyan
CPC classification number: F01D5/187 , F01D5/186 , F01D9/02 , F01D11/001 , F05D2220/31 , F05D2240/122
Abstract: Various embodiments include a steam turbine nozzle and turbomachinery including such a nozzle. In various particular embodiments, a steam turbine nozzle includes: a body having: a first sidewall and a second sidewall opposite the first sidewall; a pressure side and a suction side each extending between the first sidewall and the second sidewall; and a leading edge section at a first junction of the pressure side and the suction side, and a trailing edge section at a second junction of the pressure side and the suction side; and a bypass fluid conduit including: a channel having an opening to at least one of the first sidewall or the second sidewall; and an outlet passageway fluidly connected with the channel between the first sidewall and the second sidewall, the outlet passageway including a first opening on at least one of the pressure side of the body, the suction side of the body or the trailing edge section.
Abstract translation: 各种实施例包括蒸汽轮机喷嘴和包括这种喷嘴的涡轮机械。 在各种具体实施例中，蒸汽轮机喷嘴包括：主体，其具有：与第一侧壁相对的第一侧壁和第二侧壁; 压力侧和吸力侧，每个在所述第一侧壁和所述第二侧壁之间延伸; 以及在压力侧和吸力侧的第一接合处的前缘部分和在压力侧和吸力侧的第二接合处的后缘部分; 以及旁通流体导管，包括：通道，具有至少一个第一侧壁或第二侧壁的开口; 以及出口通道，其与所述第一侧壁和所述第二侧壁之间的通道流体连接，所述出口通道包括在所述主体的所述压力侧，所述主体的吸力侧或所述后缘部分中的至少一个上的第一开口。
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公开(公告)号：US20150010382A1
公开(公告)日：2015-01-08
申请号：US13933201
申请日：2013-07-02
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Joshy John
IPC: F01D17/10
CPC classification number: F02C3/32 , F01K5/02 , F02C3/34 , F02C6/08 , F02C6/18 , F02C9/18 , F05D2220/31 , F05D2220/3215 , F05D2260/601 , Y02E20/16
Abstract: Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation.
Abstract translation: 涡轮机气流被调制以提高在涡轮机中的部分负荷运行期间的性能。 涡轮机包括压缩机，具有多级的涡轮机和扩散器。 调节气流包括从涡轮机的上游部件提取气流，允许提取的气流进入多级的后级。 允许进入后级的气流用于在部分负载运行期间增加后级负载并改变后级的能量分布。
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