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公开(公告)号：US20150292347A1
公开(公告)日：2015-10-15
申请号：US14748322
申请日：2015-06-24
Applicant: General Electric Company
Inventor： Rohit Chouhan
CPC classification number: F01D11/127 , F01D5/225 , F05D2220/32 , F05D2230/80 , F05D2240/11 , F05D2250/283 , Y10T29/49238
Abstract: The present application provides a stage of a gas turbine engine. The stage may include a bucket extending radially about a longitudinal axis of the gas turbine engine, a shroud facing the bucket, the shroud including a fore end portion including a radially inner surface spaced a first distance from the longitudinal axis, and a forward step honeycomb seal positioned on the shroud downstream of the fore end portion and facing the bucket. The forward step honeycomb seal may include a first linear portion including a radially inner surface spaced a second distance from the longitudinal axis, and a forward step portion positioned adjacent to and downstream of the first linear portion, the forward step portion including a radially inner surface spaced a third distance from the longitudinal axis, wherein the second distance is greater than the third distance, and wherein the third distance is greater than the first distance.
Abstract translation: 本申请提供了一种燃气轮机的级。 该台可以包括围绕燃气涡轮发动机的纵向轴线径向延伸的铲斗，面向铲斗的护罩，护罩包括前端部分，前端部分包括与纵向轴线间隔开第一距离的径向内表面， 密封件定位在前端部分下游并面向铲斗的护罩上。 前进蜂窝状密封件可以包括第一直线部分，该第一直线部分包括与纵向轴线间隔第二距离的径向内表面，以及位于第一直线部分附近和下游的前部台阶部分，前部台阶部分包括径向内表面 与所述纵向轴线间隔开第三距离，其中所述第二距离大于所述第三距离，并且其中所述第三距离大于所述第一距离。
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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：US20140119923A1
公开(公告)日：2014-05-01
申请号：US13662891
申请日：2012-10-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Rohit Chouhan
IPC: F01D5/14
CPC classification number: F01D5/22
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.
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，旋转刀片包括翼型部分，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中空部分。
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公开(公告)号：US10323528B2
公开(公告)日：2019-06-18
申请号：US14789507
申请日：2015-07-01
Applicant: General Electric Company
Inventor： Soumyik Kumar Bhaumik , Rohit Chouhan
Abstract: A turbine nozzle disposed in a turbine includes a suction side extending between a leading edge of the nozzle and a trailing edge of the turbine nozzle in an axial direction and transverse to a longitudinal axis of the turbine nozzle, and extending a height of the nozzle in a radial direction along the longitudinal axis, a pressure side disposed opposite the suction side and extending between the leading edge of the turbine nozzle and the trailing edge of the turbine nozzle in the axial direction, and extending the height of the nozzle in the radial direction, and a bulge disposed on the suction side of the nozzle protruding relative to the other portion of the suction side in a direction transverse to a both the radial and axial directions.
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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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Patent Agency Ranking
公开(公告)号：US10161253B2
公开(公告)日：2018-12-25
申请号：US15093959
申请日：2016-04-08
Applicant: General Electric Company
Inventor： Rohit Chouhan
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.
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公开(公告)号：US10156145B2
公开(公告)日：2018-12-18
申请号：US14923697
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Stephen Paul Wassynger
Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade 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; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.
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公开(公告)号：US09957805B2
公开(公告)日：2018-05-01
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：US20170211407A1
公开(公告)日：2017-07-27
申请号：US15018373
申请日：2016-02-08
Applicant: General Electric Company
Inventor： Rohit Chouhan , Manjunath Chengappa
CPC classification number: F01D11/122 , F01D5/14 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2240/126 , F05D2240/129
Abstract: A turbine shroud for an axial turbine, the shroud including: an annular array of arch shaped shroud segments each configured to be mounted to an inner surface of a turbine casing, the segment having an arched seal surface aligned with tips of a last row of turbine buckets in the turbine, and vanes positioned on an inner surface of each of the shroud segments and downstream in a direction of gas flow through the last row, the vanes extending inward from the inner surface towards an axis of the turbine.
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公开(公告)号：US20170175535A1
公开(公告)日：2017-06-22
申请号：US14974155
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Randall Richard Good , Hiteshkumar Rameshchandra Mistry , Shashwat Swami Jaiswal
CPC classification number: F01D5/18 , F01D5/187 , F01D5/20 , F01D5/225 , F05D2220/32 , F05D2240/307 , F05D2240/55 , F05D2260/20 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.
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