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    Gaspath component including minicore plenums
    1.
    发明授权
    Gaspath component including minicore plenums 有权

    公开(公告)号：US10808571B2

    公开(公告)日：2020-10-20

    申请号：US15629812

    申请日：2017-06-22

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Matthew A. Devore ,  Renee J. Behlman

    IPC: F01D5/08 ,  F01D25/12 ,  F01D5/18 ,  F01D5/14

    Abstract: A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge.

    DUAL COOLING AIRFLOW TO BLADES
    2.
    发明申请
    DUAL COOLING AIRFLOW TO BLADES 审中-公开

    公开(公告)号：US20200182060A1

    公开(公告)日：2020-06-11

    申请号：US16794900

    申请日：2020-02-19

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Jonathan Ortiz

    IPC: F01D5/08 ,  F01D5/18

    Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber. A tangential onboard injector (TOBI) may be disposed in the first airflow path. A radial onboard injector (ROBI) may be disposed in the second airflow path.

    Component core with shaped edges
    5.
    发明授权
    Component core with shaped edges 有权

    公开(公告)号：US10167726B2

    公开(公告)日：2019-01-01

    申请号：US14821831

    申请日：2015-08-10

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Matthew S. Gleiner ,  Douglas C. Jenne

    IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  B22C9/10

    Abstract: A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, at least one cooling passage. The at least one cooling passage includes a first wall and a second wall bounding the at least one cooling passage, the first wall having a plurality of first surface features and the second wall having a plurality of second surface features. The plurality of first surface features and the plurality of second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the plurality of first surface features and the plurality of second surface features. The plurality of first surface features has a first profile, and the plurality of second surface features has a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

    GAS TURBINE ENGINE AIRFOIL WITH BI-AXIAL SKIN CORE
    9.
    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。

    INCIDENT TOLERANT TURBINE VANE COOLING
    10.
    发明申请
    INCIDENT TOLERANT TURBINE VANE COOLING 审中-公开
    偶然的涡轮风扇冷却

    公开(公告)号：US20160251974A1

    公开(公告)日：2016-09-01

    申请号：US15028572

    申请日：2014-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas N. Slavens ,  Matthew A. Devore

    IPC: F01D9/02 ,  F01D17/16

    CPC classification number: F01D9/023 ,  F01D5/18 ,  F01D5/188 ,  F01D9/041 ,  F01D17/162 ,  F01D25/12 ,  F05D2240/121 ,  F05D2260/201

    Abstract: A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber. The pre-impingement cavity is split into a leading edge cavity, pressure side cavity and a suction side cavity defined between an inner surface of the forward chamber and an outer surface of the forward impingement baffle.

    Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮叶片组件，包括一个包括压力侧和从前缘向后缘延伸的吸力侧的翼型件。 翼型件可绕垂直于发动机纵向轴线的轴线旋转，并且在翼型件内包括前室，并与冷却空气源连通，前冲击挡板限定前腔室内的预冲击空腔。 预冲击腔被分成前缘腔，压力侧腔和限定在前室的内表面和前冲击挡板的外表面之间的吸力侧空腔。

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