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    TURBOMACHINE ROTOR BLADE
    21.
    发明申请
    TURBOMACHINE ROTOR BLADE 审中-公开

    公开(公告)号：US20180355730A1

    公开(公告)日：2018-12-13

    申请号：US15619600

    申请日：2017-06-12

    Applicant: General Electric Company

    Inventor： Sandip Dutta ,  Joseph Anthony Weber

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/14 ,  F01D5/18 ,  F05D2240/24 ,  F05D2260/20

    Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.

    INTERIOR COOLING CHANNELS IN TURBINE BLADES
    24.
    发明申请
    INTERIOR COOLING CHANNELS IN TURBINE BLADES 审中-公开
    涡轮叶片内部冷却通道

    公开(公告)号：US20160186574A1

    公开(公告)日：2016-06-30

    申请号：US14583865

    申请日：2014-12-29

    Applicant: General Electric Company

    Inventor： Joseph Anthony Weber ,  Michael James Healy

    IPC: F01D5/18 ,  F01D5/14

    CPC classification number: F01D5/187 ,  F05D2230/11 ,  F05D2230/12 ,  F05D2230/211 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A blade for a turbine of a gas turbine engine that includes an airfoil, the airfoil having a leading edge, a trailing edge, an outboard tip, and an inboard end. The airfoil may further include a cooling configuration that includes a plurality of cooling channels for receiving and directing a coolant. The cooling channels may include a linear cooling channel and a curved cooling channel. The blade may also include a contoured shape defined by the airfoil between the inboard end and the outboard tip, with the contoured shape being configured so to include a target area inaccessible to a linear reference line extending radially from a position at the inboard end of the airfoil. The curved cooling channels may be configured to extend between an upstream end and a downstream end so to intersect the target area therebetween.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮机的叶片，其包括翼型件，所述翼型件具有前缘，后缘，外侧翼尖和内侧端部。 翼型件还可以包括冷却构造，其包括用于接收和引导冷却剂的多个冷却通道。 冷却通道可以包括线性冷却通道和弯曲的冷却通道。 叶片还可以包括由内侧端部和外侧端部之间的翼型件限定的轮廓形状，其中轮廓形状被构造成包括不能从在内侧端部处的位置处的位置径向延伸的线性参考线的目标区域 翼型。 弯曲的冷却通道可以被配置为在上游端和下游端之间延伸以与其间的目标区域相交。

    SNUBBER CONFIGURATIONS FOR TURBINE ROTOR BLADES
    25.
    发明申请
    SNUBBER CONFIGURATIONS FOR TURBINE ROTOR BLADES 审中-公开
    用于涡轮转子叶片的SNUBBER配置

    公开(公告)号：US20150176413A1

    公开(公告)日：2015-06-25

    申请号：US14136403

    申请日：2013-12-20

    Applicant: General Electric Company

    Inventor： Joseph Anthony Weber ,  Mark Andrew Jones

    IPC: F01D5/22

    CPC classification number: F01D5/225 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A rotor blade for use in a turbine of a combustion turbine engine. The rotor blade may include an airfoil having a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the root and an outboard tip. The rotor blade may further include dual snubber shrouds positioned on the airfoil. Each of the dual snubber shrouds may be configured to engage a corresponding snubber shroud on at least one neighboring rotor blade upon installation.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮机的转子叶片。 转子叶片可以包括具有凹压力侧壁和在相应的前缘和后缘之间轴向延伸并且在根部和外侧梢之间径向延伸的凸形吸力侧壁的翼型件。 转子叶片还可以包括位于翼型上的双缓冲罩。 每个双缓冲器护罩可构造成在安装时在至少一个相邻的转子叶片上接合相应的缓冲罩。

    Article, component, and method of making a component
    26.
    发明授权
    Article, component, and method of making a component 有权

    公开(公告)号：US10767501B2

    公开(公告)日：2020-09-08

    申请号：US15134758

    申请日：2016-04-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Joseph Anthony Weber ,  Srikanth Chandrudu Kottilingam ,  Brian Lee Tollison

    IPC: F01D5/04 ,  F01D9/02 ,  F01D25/00

    Abstract: An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall.

    Turbine components and method for forming turbine components
    27.
    发明授权
    Turbine components and method for forming turbine components 有权

    公开(公告)号：US10655477B2

    公开(公告)日：2020-05-19

    申请号：US15219804

    申请日：2016-07-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Gary Michael Itzel ,  Joseph Anthony Weber ,  David Edward Schick

    IPC: F01D5/18 ,  B22F5/04 ,  B33Y80/00 ,  F01D9/04 ,  F01D25/12 ,  B22F3/105

    Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.

    Turbine airfoil trailing edge coolant passage created by cover
    28.
    发明授权
    Turbine airfoil trailing edge coolant passage created by cover 有权

    公开(公告)号：US10233761B2

    公开(公告)日：2019-03-19

    申请号：US15334450

    申请日：2016-10-26

    Applicant: General Electric Company

    Inventor： Zachary John Snider ,  Gregory Thomas Foster ,  Joseph Anthony Weber ,  James Fredric Wiedenhoefer

    IPC: F01D9/06 ,  F01D5/18 ,  F01D25/08 ,  F01D5/14 ,  F01D9/04

    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.

    TURBOMACHINE IMPINGEMENT COOLING INSERT
    30.
    发明申请
    TURBOMACHINE IMPINGEMENT COOLING INSERT 审中-公开

    公开(公告)号：US20190017392A1

    公开(公告)日：2019-01-17

    申请号：US15648683

    申请日：2017-07-13

    Applicant: General Electric Company

    Inventor： Sandip Dutta ,  Kassy Moy Hart ,  Joseph Anthony Weber ,  Sean Patrick Gunning

    IPC: F01D5/18 ,  F01D25/12

    Abstract: The present disclosure is directed to an impingement insert for a turbomachine. The impingement insert includes an insert body having an inner surface, an outer surface spaced apart from the inner surface, and a thickness extending from the inner surface to the outer surface. The insert body defines a first depression extending from one of the inner surface or the outer surface into the insert body. The first depression has a diameter. The insert body further defines an impingement aperture extending from the first depression through the insert body. The impingement aperture has a length and a diameter. The thickness of the insert body is greater than the length of the impingement aperture and the diameter of the first depression is greater than the diameter of the impingement aperture.

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