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公开(公告)号：US10590774B2
公开(公告)日：2020-03-17
申请号：US14603321
申请日：2015-01-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik
Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a platform lip extending axially from the platform portion; and a plurality of voids disposed along a surface of the platform lip.
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公开(公告)号：US10301945B2
公开(公告)日：2019-05-28
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
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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公开(公告)号：US09957804B2
公开(公告)日：2018-05-01
申请号：US14973875
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Ross James Gustafson , Nicholas Alvin Hogberg
CPC classification number: F01D5/141 , F01D5/145 , F04D29/324 , F05D2220/32 , F05D2240/301 , F05D2240/304 , F05D2250/70
Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define 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 blades, at which adjacent blades 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：US09719355B2
公开(公告)日：2017-08-01
申请号：US14135884
申请日：2013-12-20
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni
CPC classification number: F01D5/14 , F01D5/225 , Y10T29/49336
Abstract: A method of manufacturing a blade for use with a rotary machine includes coupling a suction-side section of a part-span shroud to a suction-side surface of an airfoil of the blade. A first point of the airfoil suction-side surface, defined where a trailing edge of the suction-side section intersects the airfoil suction-side surface, is upstream from a second point, defined where a throat intersects the airfoil suction-side surface. A third point, defined where a leading edge of the suction-side section intersects the airfoil suction-side surface, is downstream from a fourth point, defined at a leading edge of the blade. The method also includes coupling a pressure-side section of the part-span shroud to a pressure-side surface of the airfoil. A fifth point of the airfoil pressure-side surface, defined where a trailing edge of the pressure-side section intersects the airfoil pressure-side surface, is downstream from the first point.
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公开(公告)号：US20170175536A1
公开(公告)日：2017-06-22
申请号：US14974193
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
CPC classification number: F01D5/187 , F01D5/147 , F01D5/225 , F05D2220/32 , F05D2240/305 , F05D2240/306 , F05D2250/711 , F05D2250/712 , F05D2260/20 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: A turbine rotor blade that includes an airfoil defined between a concave pressure face and a laterally opposed convex suction face, 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; an outlet segment discharges the coolant from the rotor blade at a shallow angle relative to a flow direction of a working fluid through the turbine; and an elbow segment connects the supply segment to the outlet segment and is positioned near the outboard tip of the airfoil. The elbow segment may be configured for accommodating a change of direction between the supply segment and the outlet segment.
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Patent Agency Ranking
公开(公告)号：US20170114647A1
公开(公告)日：2017-04-27
申请号：US14923693
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Gunnar Leif Siden , Zachary James Taylor
Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.
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公开(公告)号：US20160326889A1
公开(公告)日：2016-11-10
申请号：US15217212
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik
IPC: F01D5/18
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.
Abstract translation: 本发明的实施例一般涉及旋转机器，更具体地涉及涡轮机桶的至少部分的冷却。 在一个实施例中，本发明提供了一种冷却涡轮机桶的至少一部分的方法，所述方法包括：在涡轮机的运行期间，改变在从所述平台轴向延伸的平台唇缘和天使翼之间的吹扫空气的旋转速度 从涡轮机叶片的柄部分的表面轴向延伸，其中改变吹扫空气的旋转速度包括用沿着平台唇缘的径向内表面中的至少一个设置的多个湍流中断吹扫空气的流动 或柄部的表面。
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公开(公告)号：US20160326879A1
公开(公告)日：2016-11-10
申请号：US15216881
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik , Clint Luigie Ingram
CPC classification number: F01D5/082 , F01D5/145 , F01D11/001 , F01D11/02 , F05D2240/127 , F05D2240/80 , F05D2260/20 , F05D2260/941
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 beneath a platform lip extending axially from the platform, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of voids disposed along a length of an angel wing extending axially from a face of a shank portion of the turbine bucket.
Abstract translation: 本发明的实施例一般涉及旋转机器，更具体地涉及涡轮机桶的至少部分的冷却。 在一个实施例中，本发明提供了一种冷却涡轮机桶的至少一部分的方法，所述方法包括：在涡轮机运行期间，改变在从所述平台轴向延伸的平台唇缘下方的吹扫空气的旋转速度，其中， 吹扫空气的旋转速度包括用沿着涡轮机桶的柄部的表面轴向延伸的天使翼的长度设置的多个空隙中断吹扫空气的流动。
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公开(公告)号：US20160245095A1
公开(公告)日：2016-08-25
申请号：US14631409
申请日：2015-02-25
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Jason Adam Neville
CPC classification number: F01D5/187 , F01D5/141 , F01D5/146 , F01D5/20 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/304 , F05D2240/307 , F05D2260/20
Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge, wherein the pressure tip wall and the suction tip wall define a trailing edge tip thickness. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall, the squealer cavity including a trench extending fully to the tip trailing edge to form an open flow path out of the tip trailing edge. Further included is a suction side wall and a pressure side wall extending from a root portion of the turbine rotor blade to the tip portion, wherein the suction side wall and the pressure side wall define a trailing edge blade thickness, the trailing edge tip thickness being greater than the trailing edge blade thickness.
Abstract translation: 涡轮转子叶片包括具有压力顶端壁和吸入端壁，尖端前缘和尖端后缘的尖端部分，其中压力尖端壁和吸力端壁限定了后缘尖端厚度。 还包括一个至少部分地由压力尖端壁和吸力端壁限定的尖叫声腔，该尖声腔包括一个完全延伸到尖端后缘的沟槽，以形成一个从尖端后缘开出的开放流路。 进一步包括从涡轮转子叶片的根部延伸到顶端部分的吸力侧壁和压力侧壁，其中吸力侧壁和压力侧壁限定后缘叶片厚度，后缘尖端厚度为 大于后缘叶片厚度。
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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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