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公开(公告)号：US20200095871A1
公开(公告)日：2020-03-26
申请号：US16683659
申请日：2019-11-14
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：US10539032B2
公开(公告)日：2020-01-21
申请号：US15372548
申请日：2016-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sumeet Soni , Rohit Chouhan , Ross James Gustafson , Matthew Peter Scoffone
IPC: F01D9/04
Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has 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 is defined by values set forth in Table 1, where the throat distribution values are within a +/−10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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公开(公告)号：US10247013B2
公开(公告)日：2019-04-02
申请号：US14974193
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
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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公开(公告)号：US10215032B2
公开(公告)日：2019-02-26
申请号：US15088204
申请日：2016-04-01
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, 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.
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公开(公告)号：US20170130596A1
公开(公告)日：2017-05-11
申请号：US14937992
申请日：2015-11-11
Applicant: General Electric Company
Inventor： Soumyik Kumar Bhaumik , Gunnar Leif Siden , Deepesh Nanda , Rohit Chouhan
CPC classification number: F01D9/041 , F01D5/02 , F01D5/143 , F01D5/145 , F01D5/225 , F01D25/24 , F01D25/30 , F02C3/04 , F05D2220/32 , F05D2220/3215 , F05D2240/128 , F05D2240/35 , F05D2250/38
Abstract: A gas turbine includes a turbine and an axial-radial diffuser. The turbine includes a last stage airfoil section, which includes a first inner annular wall, a plurality of airfoils, a tip shroud including a first outer annular wall, and a stationary shroud including a second outer annular wall. The first inner annular wall is angled at a first inner angle average, the first outer annular wall is angled at a first outer angle average, and the second outer annular wall is angled at a second outer angle average. The axial-radial diffuser includes a third inner annular wall and a third outer annular wall, wherein the first diffuser section is disposed immediately downstream from the last stage airfoil section, wherein the third inner annular wall is angled at a third inner angle average, and the third outer annular wall is angled at a third outer angle average. The first outer angle average is greater than the third outer angle average, the first inner angle average is greater than the third inner angle average, and the third outer angle average is greater than the second outer angle average.
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Patent Agency Ranking
公开(公告)号：US09546555B2
公开(公告)日：2017-01-17
申请号：US13717265
申请日：2012-12-17
Applicant: General Electric Company
Inventor： Rohit Chouhan , Holly Renae Davis , Lakshmanan Valliappan
CPC classification number: F01D5/225 , F01D5/16 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A rotatable blade for use in a turbomachine includes an airfoil portion having a leading edge, a trailing edge a radially-inner end and a radially-outer end; a root section at to the radially-inner end of the airfoil portion, and a part-span shroud located on the airfoil portion between the root section and the radially-outer end. The part-span shroud decreases in width and thickness from decreasing in width and thickness from the airfoil portion to a contact surface adapted to engage a mating contact surface on a part-span shroud of an adjacent blade.
Abstract translation: 用于涡轮机的可旋转叶片包括具有前缘的翼型部分，后缘具有径向内端和径向外端; 位于翼型部分的径向内端的根部，以及位于根部与径向外端之间的翼型部分上的部分跨度护罩。 部分跨度的宽度和厚度从宽度和厚度从翼型部分减小到适于接合邻近叶片的部分跨度护罩上的配合接触表面的接触表面。
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7.发明申请ROTOR BLADE WITH WHEEL SPACE SWIRLERS AND METHOD FOR FORMING A ROTOR BLADE WITH WHEEL SPACE SWIRLERS 审中-公开具有轮子旋转器的转子叶片和用于形成具有轮子旋转器的转子叶片的方法公开(公告)号：US20170002673A1
公开(公告)日：2017-01-05
申请号：US15257986
申请日：2016-09-07
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Bhaumik
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.
Abstract translation: 本公开涉及一种用于形成转子叶片的转子叶片和方法。 转子叶片包括具有从顶侧径向间隔开的底侧的平台和与后缘部分轴向间隔开的前缘部分。 翼面从平台的顶侧径向向外延伸，并且从该平台的底侧径向向内延伸的柄部。 柄包括从柄的前壁轴向向外延伸的唇缘。 唇缘限定径向向内的表面和径向向外的表面和多个狭槽。 旋流叶片插入件设置在多个狭槽的各个狭槽内。 每个旋流器叶片插入件从唇部的内表面径向向内延伸并且从柄的前壁向外轴向延伸。
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公开(公告)号：US20160258301A1
公开(公告)日：2016-09-08
申请号：US14638531
申请日：2015-03-04
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal
CPC classification number: F01D5/20 , F01D5/18 , F02C3/04 , F05D2220/32 , F05D2240/307 , F05D2240/35 , F05D2250/121 , F05D2250/141 , 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. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.
Abstract translation: 涡轮转子叶片包括具有压力顶端壁和吸力端壁，尖端前缘和尖端后缘的尖端部分。 还包括至少部分地由压力顶端壁和吸力端壁限定的尖叫腔。 进一步包括至少一个由吸力端壁限定的孔，所述至少一个孔被配置为将冷却流体从呼吸器腔排出到热气体路径中，以减小鸣叫器腔内的压力。 另外还有一个主体，其具有吸力侧壁和压力侧壁，每个侧壁从涡轮转子叶片的根部延伸到顶端部分。
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公开(公告)号：US20160215625A1
公开(公告)日：2016-07-28
申请号：US14603318
申请日：2015-01-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik
CPC classification number: F01D5/147 , F01D5/08 , F01D5/081 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/14 , F01D11/001 , F01D11/006 , F01D11/02 , F05D2220/32 , F05D2240/30 , F05D2240/55 , F05D2240/80
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 shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion, the at least one angel wing including an angel wing rim extending radially upward toward the airfoil; and a plurality of voids disposed along the angel wing rim.
Abstract translation: 本发明的实施例一般涉及旋转机械，更具体地，涉及在燃气涡轮机中控制车轮间隙吹扫空气。 在一个实施例中，本发明提供一种涡轮机桶，包括：平台部分; 从平台部分径向向外延伸的翼型件; 从所述平台部分径向向内延伸的柄部; 至少一个天使翼从所述柄部的表面轴向延伸，所述至少一个天使翼包括朝向翼型件径向向上延伸的天使翼缘; 以及沿天使翼缘设置的多个空隙。
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公开(公告)号：US10544695B2
公开(公告)日：2020-01-28
申请号：US14603314
申请日：2015-01-22
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 control of wheel space purge flow 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 shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion; a platform lip extending axially from the platform portion, the platform lip disposed radially outward from the at least one angel wing; and a plurality of turbulators disposed along and extending outward from the face of the shank portion between the platform lip and the at least one angel wing.
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