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    INTERNALLY DAMPED AIRFOILED COMPONENT AND METHOD
    11.
    发明申请
    INTERNALLY DAMPED AIRFOILED COMPONENT AND METHOD 审中-公开
    内部阻尼气动元件和方法

    公开(公告)号：US20160084089A1

    公开(公告)日：2016-03-24

    申请号：US14785119

    申请日：2014-04-22

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Richard K. Hayford

    IPC: F01D5/16 ,  F01D9/04 ,  F01D25/06 ,  F01D25/12 ,  B23K15/00 ,  F04D29/54 ,  B22F3/105 ,  B22F5/04 ,  B23K26/342 ,  F01D5/18 ,  F04D29/32

    Abstract: An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.

    Abstract translation: 翼型部件包括：根部，翼型部，封闭在翼型部的一部分内的阻尼口袋和阻尼器。 翼型部分包括抽吸侧壁和压力侧壁，每个侧壁在前缘和后缘之间均匀延伸，并且在根部和翼型端之间沿翼展方向延伸。 阻尼器包括与阻尼器安装表面一体化的固定端和从阻尼器安装表面延伸到阻尼器袋中的自由端。

    GAS TURBINE ENGINE INCLUDING PNEUMATIC ACTUATOR SYSTEM
    12.
    发明申请
    GAS TURBINE ENGINE INCLUDING PNEUMATIC ACTUATOR SYSTEM 审中-公开
    气体涡轮发动机，包括气动执行器系统

    公开(公告)号：US20140298788A1

    公开(公告)日：2014-10-09

    申请号：US14174537

    申请日：2014-02-06

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Richard K. Hayford

    IPC: F02C1/02

    CPC classification number: F01D11/22 ,  F05D2270/65

    Abstract: A gas turbine engine that includes a compressor section and a pneumatic actuator system is delivered. The pneumatic actuator system includes a bleed air duct that receives bleed air from the compressor section and delivers the bleed air through an accumulator and to an actuator. The accumulator includes a chamber that attenuates a fluctuation in a pressure of the bleed air.

    Abstract translation: 提供包括压缩机部分和气动执行器系统的燃气涡轮发动机。 气动致动器系统包括排气管道，其接收来自压缩机部分的排出空气，并将排放空气通过蓄能器和致动器输送。 蓄能器包括一个衰减出气压力波动的室。

    CMC BOAS arrangement
    14.
    发明授权
    CMC BOAS arrangement 有权

    公开(公告)号：US11105214B2

    公开(公告)日：2021-08-31

    申请号：US16516977

    申请日：2019-07-19

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Thomas E. Clark

    IPC: F01D11/08 ,  F01D5/14 ,  F01D5/28

    Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend from the base portion. The first wall is circumferentially spaced from the second wall. The first and second walls extend at an angle less than 90° from the base portion. The first and second walls extend towards one another.

    CMC BOAS arrangement
    15.
    发明授权
    CMC BOAS arrangement 有权

    公开(公告)号：US11073038B2

    公开(公告)日：2021-07-27

    申请号：US16516943

    申请日：2019-07-19

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Thomas E. Clark

    IPC: F01D11/08

    Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A first hook extends from the first wall and a second hook extends from the second wall. A wedge seal is arranged between the at least two adjacent seal segments. A clip is configured to bias the wedge seal radially inward.

    Gas turbine engine blade outer air seal profile
    18.
    发明授权
    Gas turbine engine blade outer air seal profile 有权

    公开(公告)号：US10309253B2

    公开(公告)日：2019-06-04

    申请号：US14994186

    申请日：2016-01-13

    Applicant: United Technologies Corporation

    Inventor： Kevin J. Ryan ,  Terence P. Tyler, Jr. ,  Ken F. Blaney

    IPC: F02C7/12 ,  F01D25/12 ,  F02C3/04 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08

    Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

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