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    AXIAL TRANSFER TUBE
    23.
    发明申请
    AXIAL TRANSFER TUBE 有权
    轴向转管

    公开(公告)号：US20170002671A1

    公开(公告)日：2017-01-05

    申请号：US14790589

    申请日：2015-07-02

    Applicant: United Technologies Corporation

    Inventor： RYAN ALAN WAITE ,  Jeffrey Michael Jacques ,  Benjamin F. Hagan

    IPC: F01D9/06 ,  F01D25/12 ,  F16L9/00 ,  F01D9/02

    CPC classification number: F01D9/065 ,  F01D9/02 ,  F01D9/06 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/20 ,  F16L9/006 ,  Y02T50/675

    Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.

    Abstract translation: 所描述的是用于与连接到平台的燃气涡轮发动机的翼型一起使用的传送管。 传送管包括主体，主体具有限定入口的第一端，所述第一端被配置为接收流体流动，第二端限定用于流体流动的出口，主体具有弯曲部分。 传送管还包括联接到主体的第一端的第一配合面。 传送管还包括联接到主体的第二端的第二配合面。 所述第一配合面或所述第二配合面中的至少一个被配置为联接到所述外径平台的平台主体。

    GAS TURBINE ENGINE AIRFOIL WITH BI-AXIAL SKIN CORE
    24.
    发明申请
    GAS TURBINE ENGINE AIRFOIL WITH BI-AXIAL SKIN CORE 审中-公开
    气动涡轮发动机与双轴皮肤核心的气翼

    公开(公告)号：US20170002662A1

    公开(公告)日：2017-01-05

    申请号：US14789356

    申请日：2015-07-01

    Applicant: United Technologies Corporation

    Inventor： Ryan Alan Waite ,  Matthew A. Devore ,  Benjamin F. Hagan

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D9/065 ,  F05D2250/313 ,  F05D2250/75 ,  F05D2260/20 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes a body that extends in a radial direction that provides an exterior airfoil surface. The body includes pressure and suction side walls that extend from a leading edge to a trailing edge in a chord-wise direction. A core cooling passage is provided between the pressure and suction side walls and extends in the radial direction. A skin passage is arranged in one of the pressure and suction side walls between the core cooling passage and the exterior airfoil surface. The skin passage includes a first passageway that extends in the radial direction. The first passageway turns to a second passageway that extends in the chord-wise direction to terminate at an exit arranged near the trailing edge.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括沿径向延伸的主体，其提供外部翼型表面。 主体包括压力和吸力侧壁，其沿着弦向方向从前缘延伸到后缘。 核心冷却通道设置在压力侧和吸力侧壁之间，并沿径向方向延伸。 皮芯通道设置在芯冷却通道和外部翼型件表面之间的压力和吸力侧壁之一中。 皮肤通道包括沿径向方向延伸的第一通道。 第一通道转向第二通道，该第二通道沿顺时针方向延伸以终止在靠近后缘的出口处。

    FLUID TRANSPORT SYSTEM HAVING DIVIDED TRANSPORT TUBE
    25.
    发明申请
    FLUID TRANSPORT SYSTEM HAVING DIVIDED TRANSPORT TUBE 审中-公开
    具有运输管道的液体运输系统

    公开(公告)号：US20150192072A1

    公开(公告)日：2015-07-09

    申请号：US14517962

    申请日：2014-10-20

    Applicant: United Technologies Corporation

    Inventor： Benjamin F. Hagan

    IPC: F02C9/18 ,  F23R3/26 ,  F02C3/04

    CPC classification number: F23R3/26 ,  F01D9/065

    Abstract: A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages.

    Abstract translation: 用于燃气涡轮发动机的流体输送系统包括构造成提供流体的增压室，具有内部空腔的翼型件和布置成在气室和翼型的内部空腔之间传递流体的输送管。 输送管包括入口，出口，从入口延伸到出口的空腔以及将空腔分成多个流动通道的至少一个分隔壁。

    Cored airfoil platform with outlet slots
    26.
    发明授权
    Cored airfoil platform with outlet slots 有权

    公开(公告)号：US10808549B2

    公开(公告)日：2020-10-20

    申请号：US16049987

    申请日：2018-07-31

    Applicant: United Technologies Corporation

    Inventor： Benjamin F. Hagan ,  Ryan Alan Waite ,  Bryan P. Dube ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12 ,  F01D9/06 ,  F01D5/22

    Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.

    Gas turbine engine turbine vane baffle and serpentine cooling passage
    27.
    发明授权
    Gas turbine engine turbine vane baffle and serpentine cooling passage 有权

    公开(公告)号：US10465542B2

    公开(公告)日：2019-11-05

    申请号：US15708603

    申请日：2017-09-19

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Ryan Alan Waite ,  Steven Bruce Gautschi ,  Benjamin F. Hagan

    IPC: F01D9/06 ,  F01D5/18 ,  F01D25/12 ,  F01D25/14

    Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.

    Airfoil with skin core cooling
    29.
    发明授权
    Airfoil with skin core cooling 有权

    公开(公告)号：US10378381B2

    公开(公告)日：2019-08-13

    申请号：US15022943

    申请日：2014-10-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Benjamin F. Hagan ,  Ryan Alan Waite

    IPC: F01D25/12 ,  F01D9/04 ,  F04D29/54 ,  F04D29/58 ,  F01D5/18 ,  F01D9/06

    Abstract: A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.

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