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    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE
    53.
    发明公开
    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE 审中-公开
    用于燃气涡轮发动机的添加制造的燃料喷嘴芯

    公开(公告)号：EP3052784A1

    公开(公告)日：2016-08-10

    申请号：EP14851160.3

    申请日：2014-10-01

    Applicant: United Technologies Corporation

    Inventor： XU, JinQuan

    IPC: F02C7/22 ,  F23R3/28 ,  F23D11/38 ,  B22D17/20 ,  B22C9/10

    CPC classification number: B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  B22D17/20 ,  F02C7/2365 ,  F05D2230/211 ,  F05D2230/30 ,  F23D11/38 ,  F23R3/28 ,  F23R3/286

    Abstract: A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.

    Abstract translation: 一种制造用于燃气涡轮发动机燃烧器的燃料部件的方法，包括制造牺牲芯的添加剂和至少部分地围绕牺牲芯制造燃料部件主体。 牺牲芯至少部分地被去除以至少部分地限定燃料组分的内部几何形状。 用于燃气涡轮发动机燃烧器的燃料部件的添加制造的牺牲芯包括第一结构和第二结构。 第一结构至少部分地限定燃料组分的第一通道。 第二结构至少部分地限定燃料组分的第二通道。 第二结构至少部分地围绕第一结构。

    GAS TURBINE ENGINE COMPONENT FOR ACOUSTIC ATTENUATION
    57.
    发明公开
    GAS TURBINE ENGINE COMPONENT FOR ACOUSTIC ATTENUATION 审中-公开

    公开(公告)号：EP3683400A1

    公开(公告)日：2020-07-22

    申请号：EP20152685.2

    申请日：2020-01-20

    Applicant: United Technologies Corporation

    Inventor： REBA, Ramons A. ,  MORIN, Bruce L. ,  GYSLING, Daniel L. ,  THILL, Carson A. Roy ,  PAULINO, Jose R. ,  XU, JinQuan ,  MORFORD, Stephen A.

    IPC: F01D5/08 ,  F01D11/00 ,  F01D25/04 ,  F01D25/24

    Abstract: A section (100) for a gas turbine engine (20) includes a rotating structure, a stationary structure (89), and a flow guide assembly (78, 178, 278, 378) arranged generally between the rotating structure and the stationary structure (89). A flow path (80) is defined between the flow guide assembly (78, 178, 278, 378) and one of the rotating structure and the stationary structure (89). The flow guide assembly (78, 178, 278, 378) includes a plurality of apertures (82, 182, 282, 382) configured to disrupt acoustic waves of air in the flow path (80). A seal (76) is configured to establish a sealing relationship between the rotating structure and the stationary structure (89), and wherein an inlet (80a) to the flow path (80) is adjacent the seal (76). A gas turbine engine (20) and a method of disrupting acoustic waves in a flow path (80) of a gas turbine engine (20) are also disclosed.

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