-
公开(公告)号：US20200165918A1
公开(公告)日：2020-05-28
申请号：US16199353
申请日：2018-11-26
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Sylvain Pierre , Prem Venugopal
Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X′, Y′, and Z′ as set forth in Table II. The Cartesian coordinate values of X′, Y′, and Z′ are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X′, Y′, and Z′ by a height of the airfoil defined along a Z′ axis. The X′ and Y′ values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z′ coordinate value. The contour lines may be joined smoothly with one another to form the first portion.
-
2.发明授权公开(公告)号：US09458732B2
公开(公告)日：2016-10-04
申请号：US14063358
申请日：2013-10-25
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Carl Gerard Schott , Clint Luigie Ingram , Gunnar Leif Siden , Sylvain Pierre
CPC classification number: F01D9/023 , F01D5/141 , F05D2240/122 , F05D2250/182 , F05D2250/183 , F05D2250/71
Abstract: Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.
Abstract translation: 提供了用于涡轮机系统和涡轮机械的过渡管道组件。 在一个实施例中，过渡管道组件包括设置在大致环形阵列中并包括第一过渡管道和第二过渡管道的多个过渡管道。 多个过渡管道中的每一个包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 每个过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道组件还包括由第一过渡管道和第二过渡管道的通道限定的空气动力学结构。 空气动力学结构包括压力侧，吸力侧和后缘，后缘具有改进的空气动力学轮廓。
-
公开(公告)号：US10808538B2
公开(公告)日：2020-10-20
申请号：US16176275
申请日：2018-10-31
Applicant: General Electric Company
Inventor： Melbourne James Myers , Sylvain Pierre , Michael Gordon Sherman , Luke C Sponseller , Zhirui Dong , Le Trong Tran
Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
-
公开(公告)号：US20200131912A1
公开(公告)日：2020-04-30
申请号：US16176275
申请日：2018-10-31
Applicant: General Electric Company
Inventor： Melbourne James Myers , Sylvain Pierre , Michael Gordon Sherman , Luke C. Sponseller , Zhirui Dong , Le Trong Tran
Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
-
5.发明申请FIRST STAGE NOZZLE OR TRANSITION NOZZLE CONFIGURED TO PROMOTE MIXING OF RESPECTIVE COMBUSTION STREAMS DOWNSTREAM THEREOF BEFORE ENTRY INTO A FIRST STAGE BUCKET OF A TURBINE 审中-公开第一阶段喷嘴或过渡喷嘴配置为在进入涡轮机的第一阶段之前促进相关燃烧流的混合下游公开(公告)号：US20150167979A1
公开(公告)日：2015-06-18
申请号：US14109418
申请日：2013-12-17
Applicant: General Electric Company
Inventor： Gunnar Leif Siden , Scott Matthew Sparks , Clint L. Ingram , Sylvain Pierre , Neil Ristau
CPC classification number: F23R3/16 , F01D9/023 , F05D2240/122 , F05D2240/127 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F23R3/46
Abstract: The present application and the resultant patent provide a disruptive surface on a trailing edge of a stage one nozzle or transition nozzle to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine. For example, in one embodiment, a gas turbine engine may include a combustor having a combustion flow. The gas turbine engine also may include one or more airfoils forming a first stage nozzle or s transition nozzle disposed downstream of the combustor. Moreover, the gas turbine engine may include a flow disruption surface positioned about a trailing edge of the one or more airfoils to promote mixing of the combustion flow.
Abstract translation: 本申请和所得专利在阶段一喷嘴或过渡喷嘴的后缘提供破坏性表面，以在进入涡轮机的第一级斗之前促进其下游的各自燃烧流的混合。 例如，在一个实施例中，燃气涡轮发动机可以包括具有燃烧流的燃烧器。 燃气涡轮发动机还可以包括形成设置在燃烧器下游的第一级喷嘴或过渡喷嘴的一个或多个翼型件。 此外，燃气涡轮发动机可以包括围绕一个或多个翼型件的后缘定位的流动破坏表面，以促进燃烧流的混合。
-
Patent Agency Ranking
公开(公告)号：US11384640B2
公开(公告)日：2022-07-12
申请号：US16199353
申请日：2018-11-26
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Sylvain Pierre , Prem Venugopal
Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X′, Y′, and Z′ as set forth in Table II. The Cartesian coordinate values of X′, Y′, and Z′ are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X′, Y′, and Z′ by a height of the airfoil defined along a Z′ axis. The X′ and Y′ values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z′ coordinate value. The contour lines may be joined smoothly with one another to form the first portion.
-
公开(公告)号：US20210115944A1
公开(公告)日：2021-04-22
申请号：US16654496
申请日：2019-10-16
Applicant: General Electric Company
Inventor： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
-
公开(公告)号：US20200157956A1
公开(公告)日：2020-05-21
申请号：US16191614
申请日：2018-11-15
Applicant: General Electric Company
Inventor： Sylvain Pierre , Bryan David Lewis , Debdulal Das , Stephen Walter Newman
Abstract: A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
-
公开(公告)号：US10253638B2
公开(公告)日：2019-04-09
申请号：US14824953
申请日：2015-08-12
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , 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.
-
公开(公告)号：US09631500B2
公开(公告)日：2017-04-25
申请号：US14066928
申请日：2013-10-30
Applicant: General Electric Company
Inventor： Sylvain Pierre , Holly Davis Brown
CPC classification number: F01D5/225 , B23P15/006 , B23P15/04 , F01D5/187 , F01D25/12 , Y10T29/49332
Abstract: An assembly for use in a turbine engine is provided. The assembly includes a first bucket, a second bucket circumferentially adjacent to the first bucket, a shroud extending between the first and second buckets, and an aerodynamic shell substantially encircling the shroud such that a cavity is formed between the aerodynamic shell and the shroud.
-
-
-
-
-
-
-
-
-
Search Results
17
records
(took 0.014 seconds)
