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31.发明申请SYSTEM AND METHOD FOR EXHAUSTING COMBUSTION GASES FROM GAS TURBINE ENGINES 有权用于从燃气涡轮发动机排放燃烧气体的系统和方法公开(公告)号：US20150000292A1
公开(公告)日：2015-01-01
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.
Abstract translation: 一种系统包括燃气涡轮发动机，该燃气涡轮发动机包括燃烧器部分，该燃烧器部分具有构造成产生燃烧产物的一个或多个燃烧器和在上游端和下游端之间具有一个或多个涡轮级的涡轮部分。 一个或多个涡轮级由燃烧产物驱动。 燃气涡轮发动机还包括设置在涡轮部分的下游端的下游的排气部分。 排气部具有构造成接收作为废气的燃烧产物的排气通路。 燃气涡轮发动机还包括设置在排气部分中的混合装置。 混合装置被构造成将排气分成第一废气和第二废气，并且在混合区域中组合第一和第二废气以产生混合废气。
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公开(公告)号：US20140161603A1
公开(公告)日：2014-06-12
申请号：US13708238
申请日：2012-12-07
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D25/30
Abstract: An exhaust diffuser is provided having a center body having an inlet adapted for coupling to a turbine. The center body has an outer wall, and a guide member disposed inside the center body. A flow path reducing member is disposed inside the center body. The flow path reducing member is configured to be movable into a first position and a second position. The first position is an inactive position having no impact on an exit flow area of the exhaust diffuser, and the second position is a deployed position that reduces the exit flow area of the exhaust diffuser.
Abstract translation: 提供了一种排气扩散器，其具有具有适于联接到涡轮机的入口的中心体。 中心体具有外壁和设置在中心体内部的引导构件。 流路减少构件设置在中心体的内部。 流路减小构件被构造成可移动到第一位置和第二位置。 第一位置是对排气扩散器的出口流动区域没有影响的无效位置，并且第二位置是减小排气扩散器的出口流动面积的展开位置。
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公开(公告)号：US20240360837A1
公开(公告)日：2024-10-31
申请号：US18307038
申请日：2023-04-26
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Navaneeth Kishan T R
CPC classification number: F04D29/181 , F01D5/141 , F04D17/025 , F01D5/06 , F04D29/324
Abstract: An extraction impeller for an axial compressor includes first vanes having an elongated S-shape arranged on the surface of an impeller body. The first vanes extend radially from an outer flow inlet edge of the body to a flow outlet hub centered on the surface at the rotation axis. A radially inner end of each of the first vanes connects at the flow outlet hub in a direction perpendicular to a rotation axis. Second vane(s) are arranged between adjacent first vanes, and third vanes are arranged between second vanes and between first vanes and second vanes. Second vanes are radially longer than third vanes. The impeller extracts air from the axial compressor and forms an axial flow with reduced vortex whistle. When used in an axial compressor of a gas turbine system, the impeller reduces flow unsteadiness.
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公开(公告)号：US10982549B2
公开(公告)日：2021-04-20
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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公开(公告)号：US10465710B2
公开(公告)日：2019-11-05
申请号：US15279004
申请日：2016-09-28
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Sagar Kamble
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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Patent Agency Ranking
公开(公告)号：US10465709B2
公开(公告)日：2019-11-05
申请号：US15278994
申请日：2016-09-28
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Sagar Kamble
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：US10443405B2
公开(公告)日：2019-10-15
申请号：US15591242
申请日：2017-05-10
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Adam John Fredmonski
Abstract: A rotor blade includes an airfoil. The airfoil includes a leading edge and a trailing edge downstream of the leading edge. The airfoil also includes a radially outer tip with a pressure side tip rail and a suction side tip rail. A slot is formed in an aft portion of the suction side tip rail and an opening is positioned between the suction side tip rail and the pressure side tip rail at the trailing edge. Gas flows from the tip via the slot and the opening to inhibit formation of a vortex flow proximate to the suction side of the airfoil.
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公开(公告)号：US10344604B2
公开(公告)日：2019-07-09
申请号：US15159850
申请日：2016-05-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Moorthi Subramaniyan , Pradeep Patel
Abstract: A turbomachine diffuser includes a body having an inner surface defining a diffuser flow path, a plurality of stationary struts extending from the inner surface, and a plurality of flow mixing lobes arranged in an annular array on the inner surface. The plurality of flow mixing lobes is configured and disposed to guide a substantially high momentum flow toward the inner surface of the body.
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39.发明授权公开(公告)号：US10151325B2
公开(公告)日：2018-12-11
申请号：US14681441
申请日：2015-04-08
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Manjunath Bangalore Chengappa , Pradeep Patel
IPC: F01D25/24 , F01D25/30 , F01D9/04 , F04D29/54 , F01D5/14 , F04D29/68 , B23P19/00 , F01D25/28 , B64C23/06 , F01D25/16
Abstract: A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.
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公开(公告)号：US20180328212A1
公开(公告)日：2018-11-15
申请号：US16029569
申请日：2018-07-07
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D5/20 , F05D2220/31 , F05D2220/323 , F05D2240/11 , F05D2240/14 , F05D2240/30 , F05D2250/12 , F05D2250/182 , F05D2250/294
Abstract: A system for a turbomachine includes a rotor blade configured to rotate along a circumferential direction within a casing of the turbomachine and a shroud positioned outward of the rotor blade along a radial direction. The rotor blade includes a root, a tip spaced radially outward from the root, a pressure side tip rail that extends around the tip of the rotor blade along a pressure side wall, and a suction side tip rail that extends around the tip of the rotor blade along a suction side wall. The shroud includes a radially inner surface facing the pressure side tip rail and the suction side tip rail of the rotor blade and spaced from the pressure side tip rail and the suction side tip rail of the rotor blade by a clearance gap. The shroud also includes a plurality of grooves extending continuously along the circumferential direction.
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