-
公开(公告)号：US10830082B2
公开(公告)日：2020-11-10
申请号：US16029569
申请日：2018-07-07
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan
Abstract: A system for a turbomachine includes a rotor blade configured to rotate along a circumferential direction within a casing of the turbomachine and a shroud positioned outward of the rotor blade along a radial direction. The rotor blade includes a root, a tip spaced radially outward from the root, a pressure side tip rail that extends around the tip of the rotor blade along a pressure side wall, and a suction side tip rail that extends around the tip of the rotor blade along a suction side wall. The shroud includes a radially inner surface facing the pressure side tip rail and the suction side tip rail of the rotor blade and spaced from the pressure side tip rail and the suction side tip rail of the rotor blade by a clearance gap. The shroud also includes a plurality of grooves extending continuously along the circumferential direction.
-
公开(公告)号：US20200182065A1
公开(公告)日：2020-06-11
申请号：US16212950
申请日：2018-12-07
Applicant: General Electric Company
Inventor： Adam Fredmonski , Moorthi Subramaniyan
Abstract: A turbine blade for a rotary machine includes an airfoil that extends from a root to a tip along a radial span. The airfoil further includes a first sidewall and a second sidewall that are coupled together at a leading edge of the airfoil and that extend aftward to a trailing edge of the airfoil. One of the first sidewall or the second sidewall includes a tip region having an increased stagger angle that produces a non-linear, over-hanging trailing edge.
-
公开(公告)号：US20170067358A1
公开(公告)日：2017-03-09
申请号：US14845388
申请日：2015-09-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Moorthi Subramaniyan , Jaya Rao Venkata Satya Vuppala
CPC classification number: F04D19/002 , F01D17/162 , F04D29/324 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2240/12 , F05D2250/20
Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
Abstract translation: 具有基本上按照可伸缩表1中阐述的X，Y和Z的笛卡尔坐标值的标称翼型分布的制品，其中X，Y和Z的笛卡尔坐标值是可转换为 通过将X，Y和Z的笛卡尔坐标值乘以一个数字，并且其中X和Y是当通过连续弧连接时在每个Z高度处限定翼型轮廓部分的坐标，每个Z处的翼型轮廓部分 高度彼此连接以形成完整的翼型形状。
-
公开(公告)号：US09534536B2
公开(公告)日：2017-01-03
申请号：US13933201
申请日：2013-07-02
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Joshy John
CPC classification number: F02C3/32 , F01K5/02 , F02C3/34 , F02C6/08 , F02C6/18 , F02C9/18 , F05D2220/31 , F05D2220/3215 , F05D2260/601 , Y02E20/16
Abstract: Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation.
Abstract translation: 涡轮机气流被调制以提高在涡轮机中的部分负荷运行期间的性能。 涡轮机包括压缩机，具有多级的涡轮机和扩散器。 调节气流包括从涡轮机的上游部件提取气流，允许提取的气流进入多级的后级。 允许进入后级的气流用于在部分负载运行期间增加后级负载并改变后级的能量分布。
-
公开(公告)号：US20160281518A1
公开(公告)日：2016-09-29
申请号：US15171094
申请日：2016-06-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Prabakaran Modachur Krishnan , Kevin Joseph Barb , Srikanth Deshpande , Moorthi Subramaniyan
CPC classification number: F01D9/041 , F01D5/143 , F01D5/145 , F01D9/04 , F01D11/08 , F05D2240/125 , F05D2240/126 , Y02E20/16
Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.
Abstract translation: 公开了通过将泄漏流动的方向与涡轮主流的流路重新导向和/或对准来减少涡轮机中的风阻和混合损失的系统和装置。 在一个实施例中，一种装置包括：基座，其构造成连接到涡轮的隔膜; 以及径向部分，其连接到所述基部并且从所述基部朝向所述涡轮机的转子径向向内延伸，所述径向部分被定向成以与主工作流体互补的角度径向地调节工作流体的泄漏流的行进方向 涡轮机路径。
-
Patent Agency Ranking
公开(公告)号：US20150211373A1
公开(公告)日：2015-07-30
申请号：US14167788
申请日：2014-01-29
Applicant: General Electric Company
Inventor： Thangaraj SUBBAREDDYAR , Moorthi Subramaniyan , Srikeerthi Annaluri
IPC: F01D5/22
CPC classification number: F01D5/225
Abstract: A turbine bucket includes an entry dovetail; an airfoil portion extending from the entry dovetail, the airfoil portion having a leading edge, a trailing edge, a pressure side and a suction side. Radially inner- and outer-span shrouds are provided on each of the pressure side and the suction side, the part-span shrouds each having hard faces adapted to engage and slide relative to corresponding part-span shrouds on adjacent buckets.
Abstract translation: 涡轮机桶包括入口燕尾; 从入口燕尾延伸的翼型部分，翼型部分具有前缘，后缘，压力侧和吸力侧。 径向内外跨护罩设置在压力侧和吸力侧的每一个上，部分跨度护罩各自具有适于相对于相邻铲斗上的相应部跨度护罩接合和滑动的硬面。
-
17.发明申请公开(公告)号：US20140248139A1
公开(公告)日：2014-09-04
申请号：US13782036
申请日：2013-03-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Moorthi Subramaniyan , Prabakaran Modachur Krishnan
CPC classification number: F01D5/22 , F01D5/143 , F01D5/145 , F01D5/146 , F01D11/001 , F01D11/006 , F01D11/02 , F01D11/08
Abstract: Various embodiments include a turbomachine bucket having a flow interrupter, as well as related turbomachines. Various embodiments include a turbomachine bucket having: a base section sized to couple with a turbomachine rotor, the base section having a leading edge and a trailing edge opposing the leading edge; a blade section coupled to the base section and aligned to extend radially from the base section; a shroud coupled to the blade section and aligned to extend radially from the blade section; and a flow interrupter coupled to the leading edge of the base section.
Abstract translation: 各种实施例包括具有流动断续器的涡轮机桶以及相关的涡轮机。 各种实施例包括涡轮机桶，其具有：尺寸设计成与涡轮机转子耦合的基部，所述基部具有与前缘相对的前缘和后缘; 叶片部分，其联接到所述基部并且对准以从所述基部径向延伸; 联接到所述叶片部分并对准以从所述叶片部分径向延伸的护罩; 以及联接到基部的前缘的流动断流器。
-
公开(公告)号：US20140154066A1
公开(公告)日：2014-06-05
申请号：US13693610
申请日：2012-12-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Debabrata Mukhopadhyay , Steven Sebastian Burdgick , Prashant Prabhakar Sankolli , Moorthi Subramaniyan
IPC: F01D9/02
CPC classification number: F01D5/187 , F01D5/186 , F01D9/02 , F01D11/001 , F05D2220/31 , F05D2240/122
Abstract: Various embodiments include a steam turbine nozzle and turbomachinery including such a nozzle. In various particular embodiments, a steam turbine nozzle includes: a body having: a first sidewall and a second sidewall opposite the first sidewall; a pressure side and a suction side each extending between the first sidewall and the second sidewall; and a leading edge section at a first junction of the pressure side and the suction side, and a trailing edge section at a second junction of the pressure side and the suction side; and a bypass fluid conduit including: a channel having an opening to at least one of the first sidewall or the second sidewall; and an outlet passageway fluidly connected with the channel between the first sidewall and the second sidewall, the outlet passageway including a first opening on at least one of the pressure side of the body, the suction side of the body or the trailing edge section.
Abstract translation: 各种实施例包括蒸汽轮机喷嘴和包括这种喷嘴的涡轮机械。 在各种具体实施例中，蒸汽轮机喷嘴包括：主体，其具有：与第一侧壁相对的第一侧壁和第二侧壁; 压力侧和吸力侧，每个在所述第一侧壁和所述第二侧壁之间延伸; 以及在压力侧和吸力侧的第一接合处的前缘部分和在压力侧和吸力侧的第二接合处的后缘部分; 以及旁通流体导管，包括：通道，具有至少一个第一侧壁或第二侧壁的开口; 以及出口通道，其与所述第一侧壁和所述第二侧壁之间的通道流体连接，所述出口通道包括在所述主体的所述压力侧，所述主体的吸力侧或所述后缘部分中的至少一个上的第一开口。
-
19.发明申请EXHAUST DIFFUSER ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF REDIRECTING A FLOW 有权用于涡轮机系统的排气歧管装置和重新流动的方法公开(公告)号：US20140093352A1
公开(公告)日：2014-04-03
申请号：US13632752
申请日：2012-10-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sachin Kumar Rai , Richa Awasthi , Shruti Kulkarni , Moorthi Subramaniyan
IPC: F01D9/00
CPC classification number: F01D25/30 , F05D2240/12
Abstract: An exhaust diffuser arrangement for a turbine system includes an inlet for receiving a flow proximate a last stage bucket of the turbine system, the flow flowing in a first flow direction. Also included is a flow redirecting component. The flow redirecting component includes a first wall having a first side of a concave surface geometry for redirecting the flow and a second side of a convex surface geometry. The flow redirecting component also includes a second wall spaced downstream of the first wall and having at least one flow exit for reducing a boundary layer along the second side of the first wall.
Abstract translation: 用于涡轮机系统的排气扩散器装置包括用于接收靠近涡轮机系统的最后级桶的流体的入口，流体沿第一流动方向流动。 还包括流重定向组件。 流动重定向部件包括第一壁，其具有用于重新定向流动的凹面几何形状的第一侧面和凸面几何形状的第二侧面。 流动重定向部件还包括在第一壁的下游间隔开的第二壁，并具有至少一个流出口，用于沿第一壁的第二侧减小边界层。
-
公开(公告)号：US11859817B2
公开(公告)日：2024-01-02
申请号：US17113275
申请日：2020-12-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sameer Dinkar Vartak , Sreenivasa Rao Gubba , Kamesh Lakshmi Narayanan , Arun Kumar Sridharan , Ankur Maheshwari , Dragisa Ristic , Moorthi Subramaniyan
CPC classification number: F23Q13/005 , F23Q7/02 , F23C3/002 , F24B15/005 , F24D7/00 , F24D19/10
Abstract: A system and method of igniting a coal air-fuel mixture, including a burner having a burner tube operable to carry a flowing mixture of fuel and air to a furnace for combustion therein and a first flow directing device disposed within the tube, operable to direct a first portion of the flowing fuel and air mixture to a location in the burner tube. The system also includes a laser igniter within the burner tube, the laser igniter including a laser tube having a first end with a laser light input and a second end with a light output, and a laser light source operably coupled to the laser light input. The laser light source, including a laser. The laser ignitor directing photons from the light output at the location in the burner tube to ignite at least a part of the first portion of the fuel.
-
-
-
-
-
-
-
-
-
Search Results
51
records
(took 0.029 seconds)
