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公开(公告)号：US10508554B2
公开(公告)日：2019-12-17
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：US10202852B2
公开(公告)日：2019-02-12
申请号：US14942350
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
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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公开(公告)号：US10001019B2
公开(公告)日：2018-06-19
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.
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公开(公告)号：US09988917B2
公开(公告)日：2018-06-05
申请号：US14884140
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Soumyik Kumar Bhaumik , Rohit Chouhan
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D9/047 , F05D2220/32 , F05D2240/124 , F05D2240/128 , F05D2240/80 , F05D2250/28 , F05D2250/711 , F05D2250/74
Abstract: A turbine nozzle disposed in a turbine includes a suction side having a bulge, and a pressure side. The suction side and the pressure side extend opposite one another between a leading edge and a trailing edge in an axial direction transverse to a longitudinal axis of the turbine nozzle, and extends a radial direction along the longitudinal axis. The bulge is disposed on the suction side protruding relative to the other portion of the suction side in a direction transverse to both the radial and axial directions. The turbine nozzle has a first periphery defined at a first cross-section at a first location along the height of the turbine nozzle by selected coordinate sets listed in Table 1.
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公开(公告)号：US20170175555A1
公开(公告)日：2017-06-22
申请号：US14973886
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Gunnar Leif Siden , Andre Borisenko , Ibrahim Sezer
IPC: F01D9/04
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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Patent Agency Ranking
公开(公告)号：US20170175529A1
公开(公告)日：2017-06-22
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：US20170130587A1
公开(公告)日：2017-05-11
申请号：US14936253
申请日：2015-11-09
Applicant: General Electric Company
Inventor： Soumyik Kumar Bhaumik , Brian Denver Potter , Rohit Chouhan , Georgia Fleming Brunt
CPC classification number: F01D5/145 , F01D5/141 , F01D5/147 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2220/3215 , F05D2240/301 , F05D2240/35 , F05D2250/70
Abstract: A system includes a turbine airfoil configured to be disposed in a turbine. The airfoil includes a suction side, a pressure side, and a first protrusion disposed on the suction side, a second protrusion disposed on the pressure side, or both. The suction side extends between a leading edge of the turbine airfoil and a trailing edge of the turbine airfoil in an axial direction and transverse to a longitudinal axis of the turbine airfoil, and extends a height of the turbine airfoil in a radial direction along the longitudinal axis. The pressure side is disposed opposite the suction side and extends between the leading edge of the turbine airfoil and the trailing edge of the turbine airfoil in the axial direction, and extends the height of the airfoil in the radial direction. The first protrusion is disposed on the suction side of the turbine airfoil and protrudes relative to the other portion of the suction side in a first direction transverse to both the radial and axial directions. The second protrusion is disposed on the pressure side of the turbine airfoil and protrudes relative to the other portion of the pressure side in a second direction transverse to both the radial and axial directions, and opposite the first direction.
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公开(公告)号：US20160215636A1
公开(公告)日：2016-07-28
申请号：US14603314
申请日：2015-01-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik
IPC: F01D11/00
CPC classification number: F01D11/001
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.
Abstract translation: 本发明的实施例一般涉及旋转机械，更具体地，涉及在燃气轮机中控制车轮间隙吹扫流量。 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; 至少一个从所述柄部的表面轴向延伸的天使翼; 从所述平台部分轴向延伸的平台唇缘，所述平台唇缘从所述至少一个天使翼片径向向外设置; 以及多个在所述平台唇缘和所述至少一个天使翼之间沿所述柄部分的表面向外延伸的扰流器。
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公开(公告)号：US20160215624A1
公开(公告)日：2016-07-28
申请号：US14603316
申请日：2015-01-22
Applicant: General Electric Company
Inventor： Rohit Chouhan , Soumyik Kumar Bhaumik , Clint Luigie Ingram
IPC: F01D5/14
CPC classification number: F01D5/145 , F01D5/08 , F01D5/081 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/14 , F01D11/001 , F05D2260/20
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; an angel wing extending axially from a face of the shank portion; and a plurality of voids disposed along a length of the angel wing, each of the plurality of voids extending radially through the angel wing.
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; 从所述柄部的表面轴向延伸的天使翼; 以及沿着所述天使翼的长度设置的多个空隙，所述多个空隙中的每一个径向延伸穿过所述天使翼。
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公开(公告)号：US09328619B2
公开(公告)日：2016-05-03
申请号：US13662891
申请日：2012-10-29
Applicant: General Electric Company
Inventor： Rohit Chouhan
IPC: F01D5/22
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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