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    GAS TURBINE COMPONENT WITH PLATFORM COOLING
    2.
    发明申请
    GAS TURBINE COMPONENT WITH PLATFORM COOLING 审中-公开

    公开(公告)号：US20200080424A1

    公开(公告)日：2020-03-12

    申请号：US16581895

    申请日：2019-09-25

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Matthew S. Gleiner

    IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12

    Abstract: A gas turbine engine component includes an airfoil that has a leading edge and extends from a first side of a platform that has a leading edge overhang. A root portion extends from a second side of the platform opposite the first side. A cooling passage extends through the platform and beneath a trailing edge of the airfoil. The cooling passage includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the leading edge of the airfoil and the inlet is located axially upstream of the root portion in the leading edge overhang.

    COMPONENT CORE WITH SHAPED EDGES
    4.
    发明申请
    COMPONENT CORE WITH SHAPED EDGES 审中-公开
    组件芯与形状边

    公开(公告)号：US20160076382A1

    公开(公告)日：2016-03-17

    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 ,  B22C9/10 ,  F01D25/12 ,  F01D9/04 ,  F01D11/08

    CPC classification number: F01D5/186 ,  B22C9/10 ,  B22C9/106 ,  F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2260/202 ,  Y02T50/676

    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.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机部件尤其包括至少一个冷却通道。 所述至少一个冷却通道包括限定所述至少一个冷却通道的第一壁和第二壁，所述第一壁具有多个第一表面特征，所述第二壁具有多个第二表面特征。 多个第一表面特征和多个第二表面特征被布置成使得冷却通道的宽度沿着由多个第一表面特征和多个第二表面特征限定的冷却通道的长度而变化。 多个第一表面特征具有第一轮廓，并且多个第二表面特征具有第二不同轮廓。 还公开了一种用于在飞行器部件中形成冷却通道的铸芯。

    Core arrangement for turbine engine component
    6.
    发明授权
    Core arrangement for turbine engine component 有权

    公开(公告)号：US11148191B2

    公开(公告)日：2021-10-19

    申请号：US16520911

    申请日：2019-07-24

    Applicant: United Technologies Corporation

    Inventor： Matthew S. Gleiner ,  Bret M. Teller ,  James T. Auxier

    IPC: B22D25/02 ,  F01D5/14 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  B22C9/10 ,  B22C9/06 ,  B22D15/00 ,  B22D17/00

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die. A casting core and method for fabricating a gas turbine engine component is also disclosed.

    Component core with shaped edges
    9.
    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.

    OUTER DIAMETER PLATFORM COOLING HOLE SYSTEM AND ASSEMBLY
    10.
    发明申请
    OUTER DIAMETER PLATFORM COOLING HOLE SYSTEM AND ASSEMBLY 有权
    外径平台冷却孔系统和组件

    公开(公告)号：US20160245093A1

    公开(公告)日：2016-08-25

    申请号：US14627915

    申请日：2015-02-20

    Applicant: United Technologies Corporation

    Inventor： Russell Deibel ,  Matthew S. Gleiner

    IPC: F01D5/18 ,  F02C7/18 ,  F02C3/04

    CPC classification number: F02C7/18 ,  F01D5/186 ,  F01D9/041 ,  F05D2240/81 ,  F05D2260/202 ,  Y02T50/676

    Abstract: An airfoil component is described herein. The airfoil component may include an OD platform comprising a gaspath face and a non-gaspath face coupled together via a plurality of cooling holes. The airfoil component may include an airfoil extending in from the outer diameter platform. The plurality of cooling holes comprises a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of the airfoil and a pressure side of the airfoil.

    Abstract translation: 这里描述了翼型件。 机翼部件可以包括OD平台，该平台包括经由多个冷却孔连接在一起的气路面和非气道面。 机翼部件可以包括从外径平台延伸的翼型件。 多个冷却孔包括多个组的冷却孔，其设置在靠近翼型的吸力侧的外径平台和翼型的压力侧。

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