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公开(公告)号：US20170114648A1
公开(公告)日：2017-04-27
申请号：US14923697
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Stephen Paul Wassynger
CPC classification number: F01D5/187 , F01D5/02 , F01D5/225 , F01D9/02 , F05D2220/32 , F05D2240/304 , F05D2260/20
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：US20170114645A1
公开(公告)日：2017-04-27
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：US20170107835A1
公开(公告)日：2017-04-20
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 configured to be disposed in a turbine includes a suction side, a pressure side, and a bulge disposed on the suction side. The suction side extends between a leading edge and a trailing edge in an axial direction and transverse to a longitudinal axis of the turbine nozzle, and extends a height of the turbine nozzle 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 nozzle and the trailing edge of the turbine nozzle in the axial direction, and extends the height of the turbine nozzle in the radial direction. 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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34.发明申请BULGED NOZZLE FOR CONTROL OF SECONDARY FLOW AND OPTIMAL DIFFUSER PERFORMANCE 审中-公开用于控制二次流量和优化扩散器性能的膨胀喷嘴公开(公告)号：US20170002670A1
公开(公告)日：2017-01-05
申请号：US14789507
申请日：2015-07-01
Applicant: General Electric Company
Inventor： Soumyik Kumar Bhaumik , Rohit Chouhan
IPC: F01D9/04
CPC classification number: F01D9/047 , F01D5/14 , F01D5/141 , F01D5/147 , F01D9/041 , F05D2220/32 , F05D2240/128 , F05D2250/60 , F05D2250/70
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.
Abstract translation: 设置在涡轮机中的涡轮喷嘴包括在喷嘴的前缘和涡轮喷嘴的后缘之间沿轴向方向并且横向于涡轮喷嘴的纵向轴线延伸的吸力侧，并且将喷嘴的高度 沿着纵向轴线的径向方向，压力侧，其设置成与吸力侧相对并且在轴向方向上在涡轮喷嘴的前缘和涡轮喷嘴的后缘之间延伸，并且沿径向方向延伸喷嘴的高度 以及设置在喷嘴的吸入侧上的凸起，其相对于吸入侧的另一部分在横向于径向和轴向两个方向上突出。
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公开(公告)号：US09476317B2
公开(公告)日：2016-10-25
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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Patent Agency Ranking
公开(公告)号：US20160258295A1
公开(公告)日：2016-09-08
申请号：US14635352
申请日：2015-03-02
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Rohit Chouhan , Prabakaran Modachur Krishnan
IPC: F01D5/14
CPC classification number: F01D5/143 , F01D5/145 , F01D11/001 , F05D2220/31 , F05D2220/32 , F05D2240/24 , F05D2240/80 , F05D2260/97
Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the reducing mixing of packing leakage and the main flow of hot gas or steam in gas and steam turbines, respectively. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; and at least one recess extending radially inward into the platform portion, the at least one recess being disposed at an angle relative to a leading edge of the platform portion.
Abstract translation: 本发明的实施方案一般涉及旋转机器，更具体地，涉及分别在气体和蒸汽涡轮机中的填料泄漏和热气体或蒸汽的主流的减少混合。 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; 以及至少一个向内延伸到所述平台部分内的凹部，所述至少一个凹部相对于所述平台部分的前缘以一定角度设置。
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公开(公告)号：US20160215626A1
公开(公告)日：2016-07-28
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.
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; 从所述平台部分轴向延伸的平台唇缘; 以及沿着平台唇缘的表面设置的多个空隙。
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公开(公告)号：US11078797B2
公开(公告)日：2021-08-03
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：US10544681B2
公开(公告)日：2020-01-28
申请号：US15775144
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Robert Liskiewicz , Joshy John , Rohit Chouhan
IPC: F01D5/14
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 a fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. A trailing edge of the airfoil deviates from an axial plane and a circumferential plane. A corresponding turbomachine comprising a plurality of such blades is also provided.
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公开(公告)号：US10138736B2
公开(公告)日：2018-11-27
申请号：US14949544
申请日：2015-11-23
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , 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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