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    ELECTROFORMED SHEATH
    1.
    发明申请
    ELECTROFORMED SHEATH 审中-公开
    电动沙子

    公开(公告)号：US20150184306A1

    公开(公告)日：2015-07-02

    申请号：US14644954

    申请日：2015-03-11

    Applicant: United Technologies Corporation

    Inventor： Joseph Parkos, Jr. ,  James O. Hansen ,  Christopher J. Hertel ,  Andrew J. Murphy ,  Ashley P. Phillips ,  Jay Thomas Abraham

    IPC: C25D1/00

    CPC classification number: C25D1/00 ,  C25D1/02 ,  F01D5/147 ,  F04D29/324 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2240/303 ,  F05D2300/603

    Abstract: An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.

    Abstract translation: 用于保护翼型的电铸护套包括护套主体和心轴插入件。 护套主体包括前缘。 护套主体包括压力侧壁和相对的吸力侧壁，侧壁在前缘相交并且远离前缘延伸以在侧壁之间限定空腔。 护套主体包括在前缘和腔之间的头部。 心轴插入件位于压力侧和吸力侧壁之间，并且包括大致楔形的几何形状。 一种用于保护翼型件的方法包括：1）将心轴插入件固定到心轴上; 2）将护套主体电镀到心轴和心轴插入件上; 3）从护套主体中取出心轴，使得护套空腔限定在护套主体内; 和4）将翼型件固定在护套腔内。

    Electroformed sheath
    4.
    发明授权
    Electroformed sheath 有权

    公开(公告)号：US10294573B2

    公开(公告)日：2019-05-21

    申请号：US14644954

    申请日：2015-03-11

    Applicant: United Technologies Corporation

    Inventor： Joseph Parkos, Jr. ,  James O. Hansen ,  Christopher J. Hertel ,  Andrew J. Murphy ,  Ashley P. Phillips ,  Jay Thomas Abraham

    IPC: F01D5/14 ,  C25D1/00 ,  C25D1/02 ,  F04D29/32

    Abstract: An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.

    THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE
    7.
    发明申请
    THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    一种气体涡轮发动机的热管理系统

    公开(公告)号：US20160131036A1

    公开(公告)日：2016-05-12

    申请号：US14933518

    申请日：2015-11-05

    Applicant: United Technologies Corporation

    Inventor： Matthew E. Bintz ,  Charles P. Gendrich ,  John C. DiTomasso ,  Andrew J. Murphy

    IPC: F02C7/16 ,  F02C7/047

    CPC classification number: F02C7/16 ,  B64D15/00 ,  B64D15/02 ,  B64D15/06 ,  F01D25/02 ,  F01D25/162 ,  F02C7/047 ,  F02C7/12 ,  F02C7/14 ,  F02K3/06 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/98 ,  Y02T50/675

    Abstract: In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.

    Abstract translation: 在一个示例性实施例中，用于冷却发动机部件的燃气涡轮发动机系统包括发动机芯，容纳发动机芯的铁芯壳体，芯壳体前方的发动机芯驱动风扇，围绕风扇和芯壳体的机舱，以及 旁通管道限定在芯壳体的外径和机舱的内径之间。 还包括一种具有冷却剂回路的热管理系统，该冷却剂回路包括设置在机舱内径上的第一热交换器和布置在跨过旁通管的BiFi前缘的第二热交换器中的至少一个。 第一热交换器与第二热交换器热连通。

    HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING DISCHARGE PRESSURE AIR
    8.
    发明申请
    HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING DISCHARGE PRESSURE AIR 审中-公开
    高压压缩机使用放气压力空气的转子热调节

    公开(公告)号：US20160123234A1

    公开(公告)日：2016-05-05

    申请号：US14878018

    申请日：2015-10-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Matthew P. Forcier ,  Paul J. Hiester ,  Andrew J. Murphy

    IPC: F02C9/18 ,  F02C3/04 ,  F04D29/32

    CPC classification number: F02C9/18 ,  F01D5/087 ,  F01D19/02 ,  F02C3/04 ,  F02C6/08 ,  F02C7/185 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2270/114 ,  Y02T50/676

    Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of the lower temperature tapped path and the higher temperature tapped path into the bore of the disc. The valve is operable to selectively block flow of either of the lower pressure and higher pressure tapped paths to the bore of the disc, with the disc including holes to allow air from compressor chambers to communicate with the bore of the disc. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

    Abstract translation: 用于燃气涡轮发动机的压缩机包括具有叶片和盘的压缩机转子，其具有径向地位于盘的内侧的孔。 高压空气抽头包括较低的温度挖掘路径和较高的温度挖掘路径，以及用于选择性地将较低温度的攻丝路径和较高温度的攻丝路径之一输送到盘的孔中的阀。 所述阀可操作以选择性地阻挡所述盘的所述孔的所述较低压力和较高压力的任意一个路径的流动，其中所述盘包括孔，以允许来自压缩机室的空气与所述盘的孔连通。 还公开了一种燃气涡轮发动机和操作燃气涡轮发动机的方法。

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