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公开(公告)号：US09963985B2
公开(公告)日：2018-05-08
申请号：US14973886
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Gunnar Leif Siden , Andre Borisenko , Ibrahim Sezer
CPC classification number: F01D9/041 , F05D2220/32 , F05D2240/122 , F05D2250/70 , F05D2250/90
Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine includes opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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公开(公告)号：US09885243B2
公开(公告)日：2018-02-06
申请号：US14923685
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Zachary James Taylor
CPC classification number: F01D5/18 , F01D5/02 , F01D5/187 , F01D5/225 , F01D9/02 , F01D11/08 , F01D17/105 , F05D2220/32 , F05D2260/20
Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to the base, extending radially outward from the base, and including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; and a plurality of radially extending cooling passageways within the body; and a shroud coupled to the blade radially outboard of the blade, including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within the body; and an outlet path extending at least partially circumferentially through the shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within the body.
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公开(公告)号：US20170175557A1
公开(公告)日：2017-06-22
申请号：US14974176
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Manjunath Bangalore Chengappa , Soumyik Kumar Bhaumik
CPC classification number: F01D11/001 , F01D5/02 , F01D5/12 , F01D9/041 , F05D2220/32 , F05D2240/126 , F05D2240/80
Abstract: A gas turbine having a seal sealing a trench cavity defined between a stator inboard face and rotor inboard face. The seal may include a stator overhang that extends axially toward the rotor inboard face. The stator overhang may include an overhang topside, an overhang underside, and an overhang face that is defined therebetween. The trench cavity seal may include a platform lip extending axially from the rotor inboard face toward the stator inboard face and circumferentially spaced turbulators extending axially from the rotor inboard face. An outboard edge and an inboard edge of the stator overhang axially jut such that, therebetween, a recessed pocket on the overhang face is formed. The platform lip may radially overlaps the recessed pocket on the overhang face so to form a multiple switch-back flowpath.
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公开(公告)号：US20170175530A1
公开(公告)日：2017-06-22
申请号：US14973894
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
CPC classification number: F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.
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公开(公告)号：US20170138203A1
公开(公告)日：2017-05-18
申请号：US14942350
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
CPC classification number: F01D5/187 , F01D5/186 , F01D5/225 , F05D2220/30 , F05D2230/10 , F05D2230/60 , F05D2240/30 , F05D2260/202
Abstract: A rotor blade includes an airfoil portion that extends in a radial direction from a root end to a tip end. A plurality of internal airfoil cooling passages is defined in the airfoil portion. The rotor blade also includes a tip shroud. The tip shroud includes a shroud plate coupled to the tip end. A plurality of tip shroud cooling passages is defined within the shroud plate. Each of the tip shroud cooling passages extends within the shroud plate in a direction generally transverse to the radial direction. Each tip shroud passage includes an inlet coupled in flow communication with at least one of the airfoil cooling passages, and an exit opening defined in, and extending therethrough, a radially outer surface of the tip shroud. The exit opening is coupled in flow communication with the inlet.
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Patent Agency Ranking
公开(公告)号：US20170058680A1
公开(公告)日：2017-03-02
申请号：US14843069
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal
CPC classification number: F01D5/20 , F01D5/18 , F05D2220/32 , F05D2240/306 , F05D2240/307 , F05D2260/221 , Y02T50/673
Abstract: A rotor blade for a turbine of a gas turbine system. The rotor blade may include: an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery, wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge; a tip that defines an outer radial end of the airfoil, wherein the tip included a cap on which an outboard projecting rail defines a tip cavity; and a rail gap formed through an aftward section of the rail.
Abstract translation: 一种用于燃气轮机系统的涡轮的转子叶片。 转子叶片可以包括：翼型件，其包括压力侧壁和限定外周边的吸力侧壁，其中翼型件的压力侧壁和抽吸侧壁沿着前缘和后缘连接; 限定所述翼型件的外径向端部的尖端，其中所述尖端包括盖，所述外侧突出轨道限定在所述顶盖腔体上; 以及通过轨道的后部形成的轨道间隙。
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公开(公告)号：US20160222797A1
公开(公告)日：2016-08-04
申请号：US15093959
申请日：2016-04-08
Applicant: General Electric Company
Inventor： Rohit Chouhan
CPC classification number: F01D5/187 , F01D5/225 , F01D5/28 , F04D29/324 , F05D2220/31 , F05D2230/237 , F05D2250/185 , F05D2260/20 , F05D2260/96 , F05D2300/175
Abstract: A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion having a plurality of radial cooling passages extending longitudinally therein, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises at least one hollow passage fluidly connected to at least one radial cooling passage of the plurality of radial cooling passages.
Abstract translation: 公开了一种用于涡轮机中的旋转叶片。 在一个实施例中，旋转叶片包括具有在其中纵向延伸的多个径向冷却通道的翼型部分，固定到翼型部分的第一端的根部部分和固定到翼型部分的第二端的末端部分， 第二端与第一端相对。 部分跨度护罩固定在尖端部分和根部部分之间的翼型部分，其中部分跨度护罩还包括流体地连接到多个径向冷却通道的至少一个径向冷却通道的至少一个中空通道。
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公开(公告)号：US20160215629A1
公开(公告)日：2016-07-28
申请号：US15088204
申请日：2016-04-01
Applicant: General Electric Company
Inventor： Rohit Chouhan
CPC classification number: F01D5/187 , F01D5/225 , F01D5/28 , F04D29/324 , F05D2220/31 , F05D2230/237 , F05D2250/185 , F05D2260/20 , F05D2260/96 , F05D2300/175
Abstract: A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises a hollow portion, wherein the hollow portion is devoid of any coupling structure therein.
Abstract translation: 公开了一种用于涡轮机中的旋转叶片。 在一个实施例中，旋转叶片包括翼型部分，固定到翼型部分的第一端的根部部分和固定到翼型部分的第二端的末端部分，第二端部与第一端部相对。 部分跨度护罩固定在前端部分和根部部分之间的翼型部分，其中部分跨度护罩还包括中空部分，其中中空部分中没有任何联接结构。
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公开(公告)号：US10815808B2
公开(公告)日：2020-10-27
申请号：US15217212
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik
IPC: F01D11/00
Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the cooling of at least portions of a turbine bucket. In one embodiment, the invention provides a method of cooling at least a portion of a turbine bucket, the method comprising: during operation of a turbine, altering a swirl velocity of purge air between a platform lip extending axially from the platform and an angel wing extending axially from a face of a shank portion of the turbine bucket, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of turbulators disposed along at least one of a radially inner surface of the platform lip or the face of the shank portion.
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50.发明授权公开(公告)号：US10738638B2
公开(公告)日：2020-08-11
申请号：US15257986
申请日：2016-09-07
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Bhaumik
IPC: F01D11/00
Abstract: The present disclosure is directed to a rotor blade and method for forming the rotor blade. The rotor blade includes a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion. An airfoil extends radially outwardly from the top side of the platform and a shank extends radially inwardly from the bottom side of the platform. The shank includes a lip that extends axially outwardly from a forward wall of the shank. The lip defines a radially inward surface and a radially outward surface and a plurality of slots. Swirler vane inserts are disposed within respective slots of the plurality of slots. Each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank.
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