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    COMBUSTOR WALL FOR A GAS TURBINE ENGINE AND METHOD OF ACOUSTIC DAMPENING
    32.
    发明申请
    COMBUSTOR WALL FOR A GAS TURBINE ENGINE AND METHOD OF ACOUSTIC DAMPENING 审中-公开
    用于气体涡轮发动机的COMBUSTOR墙和声音阻尼的方法

    公开(公告)号：US20160153658A1

    公开(公告)日：2016-06-02

    申请号：US14805963

    申请日：2015-07-22

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F23R3/00 ,  F02C7/24 ,  F23R3/04

    CPC classification number: F23R3/002 ,  F02C7/24 ,  F23M20/005 ,  F23R3/04 ,  F23R2900/00014 ,  F23R2900/03042 ,  F23R2900/03043 ,  Y02T50/675

    Abstract: A vascular wall of a combustor that may be for a gas turbine engine includes a first face defining at least in-part a combustion chamber, a second face defining at least in-part a cooling air plenum, and a vascular lattice structure located between the first and second faces for distributing cooling air from the plenum and to the chamber. The vascular lattice structure may be configured to enhance cooling air flow where needed whiling providing structural support. The orientation of the vascular lattice structure may further contribute toward acoustic dampening.

    Abstract translation: 可用于燃气涡轮发动机的燃烧器的血管壁包括至少部分地限定燃烧室的第一表面，至少部分地限定冷却空气压力室的第二表面，以及位于 第一和第二面用于将冷却空气从集气室和室分配。 血管晶格结构可以被配置为在提供结构支撑的需要的时候增强冷却空气流。 血管晶格结构的取向可能进一步有助于声学阻尼。

    Airfoil assembly with paired endwall contouring
    34.
    发明授权
    Airfoil assembly with paired endwall contouring 有权
    具有成对端壁轮廓的翼型组件

    公开(公告)号：US09188017B2

    公开(公告)日：2015-11-17

    申请号：US13718213

    申请日：2012-12-18

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F01D9/04 ,  F01D5/14

    CPC classification number: F01D9/041 ,  F01D5/143 ,  Y02T50/673

    Abstract: An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow.

    Abstract translation: 公开了一种翼型组件。 翼型组件可以包括一系列翼型件，例如在ID端壁和基本上同心的OD端壁之间径向延伸的叶片。 翼型件在周向间隔开并且在相邻翼型之间限定多个流体流动通道。 ID端壁和OD端壁定义轮廓区域以优化通过通道的流体流动。 ID端壁轮廓区域和OD端壁轮廓区域之间的几何关系确保了喉部区域在流体流动方向上通常增加或减小。

    COOLED FUEL INJECTOR SYSTEM FOR A GAS TURBINE ENGINE AND METHOD FOR OPERATING THE SAME
    35.
    发明申请
    COOLED FUEL INJECTOR SYSTEM FOR A GAS TURBINE ENGINE AND METHOD FOR OPERATING THE SAME 审中-公开
    用于气体涡轮发动机的冷却燃料喷射器系统及其操作方法

    公开(公告)号：US20150323186A1

    公开(公告)日：2015-11-12

    申请号：US14707790

    申请日：2015-05-08

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F23R3/28 ,  F02C7/18 ,  F02C6/08

    CPC classification number: F02C7/18 ,  F02C6/08 ,  F02C7/224 ,  F05D2260/204 ,  F05D2260/213 ,  F23R3/283 ,  Y02T50/676

    Abstract: A cooled fuel injector system of a combustor section of a gas turbine engine is provided. At least a part of the fuel injector system is exposed to core gas flow traveling through the engine. The cooled fuel injector system includes a source of a first cooling fluid and a fuel injector system component. The first cooling fluid is at a temperature lower than a temperature of the core gas flow proximate the fuel injector system. The fuel injector system component includes a vascular engineered structure lattice (VESL) structure, which VESL structure is in fluid communication with the source of the cooling fluid.

    Abstract translation: 提供了一种燃气涡轮发动机的燃烧器部分的冷却燃料喷射器系统。 燃料喷射器系统的至少一部分暴露于穿过发动机的核心气流。 冷却的燃料喷射器系统包括第一冷却流体源和燃料喷射器系统部件。 第一冷却流体的温度低于靠近燃料喷射器系统的核心气流的温度。 燃料喷射器系统部件包括血管工程结构晶格（VESL）结构，VESL结构与冷却流体源流体连通。

    PLATFORM WITH CURVED EDGES
    37.
    发明申请
    PLATFORM WITH CURVED EDGES 有权
    平台与曲折边

    公开(公告)号：US20150315916A1

    公开(公告)日：2015-11-05

    申请号：US14652657

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu

    IPC: F01D5/14 ,  F01D5/02 ,  F01D9/04

    CPC classification number: F01D5/147 ,  F01D5/021 ,  F01D5/143 ,  F01D5/145 ,  F01D9/02 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/80 ,  Y02T50/673

    Abstract: A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge to the suction side of the airfoil and a second curved edge to the pressure side of the airfoil. The first and second curved edges extend along a surface of the platform having a neutral elevation with respect to a reference axisymmetrical platform surface for the gas turbine engine.

    Abstract translation: 燃气涡轮发动机部件包括翼型件和平台。 翼型件具有压力侧和相对的吸力侧。 平台连接到翼型件，并且具有到翼型的吸入侧的第一弯曲边缘和到翼型的压力侧的第二弯曲边缘。 第一和第二弯曲边缘沿着平台的表面延伸，具有相对于燃气涡轮发动机的参考轴对称平台表面的中立高度。

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