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    Turbine blade
    1.
    发明授权
    Turbine blade 有权

    公开(公告)号：US10370978B2

    公开(公告)日：2019-08-06

    申请号：US14884114

    申请日：2015-10-15

    Applicant: General Electric Company

    Inventor： Matthew Lee Krumanaker ,  Steven Robert Brassfield ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

    IPC: F01D5/18 ,  F01D5/30 ,  F01D9/04 ,  F01D25/12

    Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

    Turbine blade
    3.
    发明授权
    Turbine blade 有权

    公开(公告)号：US10364681B2

    公开(公告)日：2019-07-30

    申请号：US14884057

    申请日：2015-10-15

    Applicant: General Electric Company

    Inventor： Matthew Lee Krumanaker ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

    IPC: F01D5/18

    Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.

    Turbine engine component with diffuser holes
    4.
    发明授权
    Turbine engine component with diffuser holes 有权

    公开(公告)号：US10030525B2

    公开(公告)日：2018-07-24

    申请号：US14661975

    申请日：2015-03-18

    Applicant: General Electric Company

    Inventor： Robert Frederick Bergholz

    IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00

    Abstract: A turbine component includes a component wall with inner and outer surfaces wherein a diffuser hole passes through the component wall between the inner surface and the outer surface. The diffuser hole has a hole axis and includes: a metering section extending from an inlet at the inner surface to a junction plane between the inner and outer surfaces; and a diffuser section extending from the junction plane to an outlet at the outer surface, and increasing in flow area from the junction plane to the outlet, the diffuser section having an upstream portion defining a first area ratio and a downstream portion defining a second area ratio different from the first area ratio.

    ENGINE COMPONENT FOR A GAS TURBINE ENGINE
    5.
    发明申请
    ENGINE COMPONENT FOR A GAS TURBINE ENGINE 审中-公开
    发动机组件用于气体涡轮发动机

    公开(公告)号：US20170051674A1

    公开(公告)日：2017-02-23

    申请号：US14829678

    申请日：2015-08-19

    Applicant: General Electric Company

    Inventor： Robert Francis Manning ,  Ronald Scott Bunker ,  Robert Frederick Bergholz ,  Robert David Briggs

    IPC: F02C7/18

    CPC classification number: F02C7/18 ,  F01D5/186 ,  F05D2250/294 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.

    Abstract translation: 用于燃气涡轮发动机的发动机部件包括膜冷却凹部，其包括限定步骤的轮廓部分。 面向热燃烧气体的热表面和面向冷却流体流的冷却表面通过通过发动机部件的通道流体耦合。 通道还包括冷却表面中的入口和台阶中的出口。 入口，通道和出口被定向成使得流过通道并离开出口的冷却流体在轮廓部分内扩散以防止与热流体流过度混合。

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