中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

9 records (took 0.024 seconds)

    GROUNDING SLEEVE
    1.
    发明申请
    GROUNDING SLEEVE 审中-公开
    接地套管

    公开(公告)号：WO2014150253A1

    公开(公告)日：2014-09-25

    申请号：PCT/US2014/022724

    申请日：2014-03-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ANDERSON, Carney R. ,  DITOMASSO, John C.

    IPC: H01R4/66

    CPC classification number: B64D45/02 ,  F16B19/02 ,  F16B2001/0064 ,  H01R4/308 ,  H01R4/64 ,  H01R2201/26 ,  H02G13/40

    Abstract: A grounding sleeve for grounding an electrically insulated element disposed between two metal components includes an annular body extending between a first end and a second end. At least one window is formed in the annular body between the first end and the second end.

    Abstract translation: 用于将布置在两个金属部件之间的电绝缘元件接地的接地套筒包括在第一端和第二端之间延伸的环形体。 在第一端和第二端之间的环形体中形成至少一个窗口。

    TANDEM ROTOR DISK APPARATUSES AND CORRESPONDING GAS TURBINE ENGINE
    4.
    发明公开
    TANDEM ROTOR DISK APPARATUSES AND CORRESPONDING GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3425164A1

    公开(公告)日：2019-01-09

    申请号：EP18170398.4

    申请日：2018-05-02

    Applicant: United Technologies Corporation

    Inventor： DITOMASSO, John C. ,  FORCIER, Matthew P.

    IPC: F01D5/14 ,  F04D29/32 ,  F01D5/30 ,  F01D5/34 ,  F04D29/64

    Abstract: A tandem rotor disk apparatus (100) may include a rotor disk body (110; 210; 310; 410; 510; 610; 710; 810) concentric about an axis (A-A'). The tandem rotor disk apparatus (100) may also include a first blade (121; 221; 321; 421; 521; 621; 721; 821) extending radially outward of the rotor disk body (110; 210; 310; 410; 510; 610; 710; 810) and a second blade (122; 222; 322; 422; 522; 622; 722; 822) extending radially outward of the rotor disk body (110; 210; 310; 410; 510; 610; 710; 810). The first blade (121; 221; 321; 421; 521; 621; 721; 821) maybe offset from the second blade (122; 222; 322; 422; 522; 622; 722; 822) in a direction parallel to the axis (A-A'). The tandem rotor disk apparatus (100) may be implemented in a gas turbine engine (20) with no intervening stator vane stages disposed between the first blade (121; 221; 321; 421; 521; 621; 721; 821) and the second blade (122; 222; 322; 422; 522; 622; 722; 822). The tandem rotor disk apparatus (100) may include two separate rotor disk bodies (110; 210; 310; 410; 510; 610; 710; 810).

    UPPER BIFI FRAME FOR A GAS TURBINE ENGINE AND METHOD OF PREVENTING AIR LEAKAGE
    5.
    发明公开
    UPPER BIFI FRAME FOR A GAS TURBINE ENGINE AND METHOD OF PREVENTING AIR LEAKAGE 审中-公开
    用于燃气轮机发动机UPPER BIFI框架和处理漏气防止

    公开(公告)号：EP3045708A1

    公开(公告)日：2016-07-20

    申请号：EP16151755.2

    申请日：2016-01-18

    Applicant: United Technologies Corporation

    Inventor： RIOS, Joseph ,  DITOMASSO, John C.

    IPC: F02K3/06 ,  F02C7/20 ,  B64D27/26

    CPC classification number: B64D29/06 ,  B64D27/12 ,  B64D27/26 ,  B64D2027/264 ,  F02C7/20 ,  F02C7/28 ,  F02K3/06

    Abstract: An upper bifurcation (bifi) frame (100) for providing an aerodynamic fairing around a pylon and for preventing air leakage in a gas turbine engine (20) including an engine casing (112) and a fan case (160) is provided. The upper bifi frame includes a forward fairing (110) having a forward fairing midsection (111) extending between the engine casing and the fan case. The forward fairing has a forward fairing first end (114) including a flange (113) configured to couple to the engine casing. The forward fairing has a forward fairing second end (116) extending from the forward fairing midsection and configured to couple to the fan case. At least one aft seal (118) is secured to the forward fairing and forms a seal therewith. A wedge seal (140) is coupled to the forward fairing and the at least one aft seal and is operative to prevent air leakage to a pylon that is secured to the engine casing.

    Abstract translation: 提供了一种上分叉（BIFI）帧（100），用于在气动整流罩围绕塔架提供用于预防和在燃气涡轮发动机（20）的空气泄漏包括发动机壳体（112）和一个风扇壳体（160）。 上部BIFI框架包括具有前整流罩中间部分（111）的发动机壳体和风扇壳体之间延伸的前整流罩（110）。 正向整流罩具有前整流罩第一端部（114）包括被配置为耦合到所述发动机壳体的凸缘（113）。 正向整流罩具有前整流罩第二端部（116）从所述前向整流罩中部延伸，并且被配置为耦合到所述风扇壳。 至少一个后密封件（118）被固定到前整流罩和形成密封在那里。 楔形密封件（140）被耦合到所述前整流罩和所述至少一个后密封件，并且可操作以防止空气泄漏到挂架也被固定到所述发动机壳体。

    GROUNDING SLEEVE
    6.
    发明公开
    GROUNDING SLEEVE 审中-公开
    接地套管

    公开(公告)号：EP2973869A1

    公开(公告)日：2016-01-20

    申请号：EP14769073.9

    申请日：2014-03-10

    Applicant: United Technologies Corporation

    Inventor： ANDERSON, Carney R. ,  DITOMASSO, John C.

    IPC: H01R4/66

    CPC classification number: B64D45/02 ,  F16B19/02 ,  F16B2001/0064 ,  H01R4/308 ,  H01R4/64 ,  H01R2201/26 ,  H02G13/40

    Abstract: A grounding sleeve for grounding an electrically insulated element disposed between two metal components includes an annular body extending between a first end and a second end. At least one window is formed in the annular body between the first end and the second end.

    Abstract translation: 用于使设置在两个金属部件之间的电绝缘元件接地的接地套管包括在第一端部和第二端部之间延伸的环形主体。 在第一端和第二端之间的环形主体中形成至少一个窗口。

    GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE
    8.
    发明公开
    GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE 审中-公开
    VORDERE ZENTRALEKÖRPERARCHITEKTURFÜRGASTURBINENMOTOR

    公开(公告)号：EP3056693A1

    公开(公告)日：2016-08-17

    申请号：EP16155879.6

    申请日：2016-02-16

    Applicant: United Technologies Corporation

    Inventor： DITOMASSO, John C. ,  REINHARDT, Gregory E.

    IPC: F01D25/24

    CPC classification number: F04D29/542 ,  F01D25/162 ,  F01D25/243 ,  F01D25/28 ,  F02C7/20 ,  F04D29/644 ,  F05D2250/11

    Abstract: A center body support (64) for a gas turbine engine (20) includes an outer annular wall (68). An aft flange (72) extends radially outward from the outer annular wall (68). A brace (69) interconnects the aft flange (72) to a forward portion (74) of the outer annular wall (68). The aft flange (72), brace (69) and forward portion (74) of the outer annual wall (68) provide a unitary, one-piece structure.

    Abstract translation: 用于燃气涡轮发动机（20）的中心体支撑件（64）包括外环形壁（68）。 后凸缘（72）从外环形壁（68）径向向外延伸。 支撑杆（69）将后凸缘（72）与外环形壁（68）的前部（74）相互连接。 外部年壁（68）的后凸缘（72），支架（69）和前部（74）提供整体的单件式结构。

    THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE
    9.
    发明公开
    THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    FÄRMEMANAGEMENTSYSTEMFÜREINE GASTURBINE

    公开(公告)号：EP3018304A1

    公开(公告)日：2016-05-11

    申请号：EP15193026.0

    申请日：2015-11-04

    Applicant: United Technologies Corporation

    Inventor： BINTZ, Matthew E. ,  GENDRICH, Charles P. ,  DITOMASSO, John C. ,  MURPHY, Andrew J.

    IPC: F01D25/16 ,  F02K3/06 ,  F02C7/12 ,  F02C7/18 ,  F02C7/047

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

    Abstract: A gas turbine engine system for cooling engine components (290; 390) includes an engine core (70; 110; 210; 310), a core housing (112) containing the engine core (70; 110; 210; 310), an engine core driven fan (42) forward of the core housing (112), a nacelle (120; 220; 320) surrounding the fan (42) and the core housing (112), and a bypass duct (130; 230; 330) defined between an outer diameter (134; 234; 334) of the core housing (112) and an inner diameter (132; 232; 332) of the nacelle (120; 220; 320). A thermal management system having a coolant circuit includes at least one of a first heat exchanger (160; 260; 360) disposed on the inner diameter (132; 232; 332) of the nacelle (120; 220; 320) and a second heat exchanger (180; 280; 380) disposed on a leading edge of a bifurcation (BiFi) (170; 270; 370) spanning the bypass duct (130; 230; 330). The first heat exchanger (160; 260; 360) is in thermal communication with the second heat exchanger (180; 280; 380).

    Abstract translation: 一种用于冷却发动机部件（290; 390）的燃气涡轮发动机系统，包括发动机机芯（70; 110; 210; 310），包含发动机机芯（70; 110; 210; 310）的铁芯壳体（112） 所述芯壳体（112）向前的核心驱动风扇（42），围绕所述风扇（42）和所述芯壳体（112）的机舱（120; 220; 320） 在所述机芯壳体（112）的外径（134; 234; 334）与所述机舱（120; 220; 320）的内径（132; 232; 332）之间。 具有冷却剂回路的热管理系统包括设置在机舱（120; 220; 320）的内径（132; 232; 332）上的第一热交换器（160; 260; 360）和第二热交换器 交换器（180; 280; 380），其布置在跨越所述旁路管道（130; 230; 330）的分叉（BiFi）（170; 270; 370）的前缘上。 第一热交换器（160; 260; 360）与第二热交换器（180; 280; 380）热连通。

Patent Agency Ranking