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    MODULAR COMPRESSOR DISCHARGE SYSTEM
    1.
    发明申请
    MODULAR COMPRESSOR DISCHARGE SYSTEM 审中-公开

    公开(公告)号：WO2020123273A1

    公开(公告)日：2020-06-18

    申请号：PCT/US2019/064835

    申请日：2019-12-06

    Applicant: CARRIER CORPORATION

    Inventor： TETU, Lee G.

    IPC: F04B39/00 ,  F04C29/06

    Abstract: A method of assembling a compressor system includes attaching at least two pulsation damper stages to a discharge port on a compressor, and attaching additional pulsation dampening stages if additional stages are desired. A compressor and discharge system is also disclosed.

    TIE ROD CONNECTION FOR MID-TURBINE FRAME
    2.
    发明申请
    TIE ROD CONNECTION FOR MID-TURBINE FRAME 审中-公开

    公开(公告)号：WO2015156882A3

    公开(公告)日：2015-10-15

    申请号：PCT/US2015/012128

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： VO, Tuan David ,  LEES, Alan

    IPC: F01D25/28 ,  F02C7/20

    Abstract: A mid-turbine frame for use in a gas turbine engine comprises at least one vane extending between a vane inner platform and a vane outer platform, and an inner case radially inward of the inner platform. A plurality of tie rods extend from a platform radially inward of the inner case to a radially outer location which is secured by a mount member. The tie rods are secured in the inner case by a forward bolt, and at least one rear bolt, with the forward bolt extending along an axis which is non-parallel to a center axis of the inner case. A gas turbine engine and a method for assembling a mid-turbine frame are also disclosed.

    MULTI-MATERIAL TURBINE AIRFOIL
    3.
    发明申请
    MULTI-MATERIAL TURBINE AIRFOIL 审中-公开
    多材料涡轮机空气

    公开(公告)号：WO2015108592A2

    公开(公告)日：2015-07-23

    申请号：PCT/US2014/061916

    申请日：2014-10-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROBERGE, Gary D.

    IPC: F01D5/14 ,  F01D5/28

    CPC classification number: F01D5/282 ,  B23P15/04 ,  F01D5/147 ,  F01D5/18 ,  F01D5/284 ,  F01D9/041 ,  F01D25/005 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2260/36 ,  F05D2300/5023 ,  F05D2300/522 ,  Y02T50/672

    Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.

    Abstract translation: 涡轮机部件包括平台和从平台径向延伸并从前缘延伸到后缘的翼型件。 前缘部分限定翼型件的前缘和包括后缘的后缘部分。 前缘部分和后缘部分之一也包括平台。 前缘部分由不同于形成后缘部分的第二材料的第一材料形成。 第一材料具有比第二材料高至少100°F的工作温度能力。 还公开了一种燃气涡轮发动机。

    TRANSFER BEARING FOR GEARED TURBOFAN
    4.
    发明申请
    TRANSFER BEARING FOR GEARED TURBOFAN 审中-公开
    用于齿轮传动的传动轴承

    公开(公告)号：WO2015094539A1

    公开(公告)日：2015-06-25

    申请号：PCT/US2014/066083

    申请日：2014-11-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： MCCUNE, Michael E.

    IPC: F02C7/06 ,  F01D25/18 ,  F01D25/16

    CPC classification number: F16H57/0479 ,  F01D25/16 ,  F01D25/183 ,  F01D25/186 ,  F02C7/06 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H57/043 ,  F16H57/0486

    Abstract: A gear reduction for a gas turbine engine comprises a carrier driven to rotate gears. The gears are supported by journal bearings. The carrier extends through a transfer bearing, which provides oil to passages within the carrier to supply oil to the gears and to the journal bearings. A device limits leakage oil from the transfer bearing to axial ends of the transfer bearing to a controlled amount. A gas turbine engine is also disclosed.

    Abstract translation: 用于燃气涡轮发动机的齿轮减速器包括被驱动以旋转齿轮的载体。 齿轮由轴颈轴承支撑。 承载件延伸通过传送轴承，该传送轴承为载体内的通道提供油以向齿轮和轴颈轴承供应油。 一种装置将传输轴承的泄漏油限制到转移轴承的轴向端部到受控的量。 还公开了一种燃气涡轮发动机。

    FAN PLATFORM WITH LEADING EDGE TAB
    6.
    发明申请
    FAN PLATFORM WITH LEADING EDGE TAB 审中-公开
    风扇平台与领先的边缘选项卡

    公开(公告)号：WO2015053848A2

    公开(公告)日：2015-04-16

    申请号：PCT/US2014/049847

    申请日：2014-08-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ALARCON, Andrew G.

    IPC: F01D5/30 ,  F01D5/02 ,  F02K3/06

    CPC classification number: F01D11/008 ,  F01D5/02 ,  F01D5/3007 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/80 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.

    Abstract translation: 用于燃气涡轮发动机的平台具有外表面和内表面。 内表面设置有用于将平台安装到转子的安装位置。 平台从前缘延伸到后缘，并在吸力壁和压力壁之间延伸。 圆周方向限定在吸入壁和压力壁之间。 翼片从平台沿吸力壁和压力壁之一的圆周向外延伸。 当平台安装时，突片具有周向最外部分，该部分将邻接相邻平台的内表面。 还公开了风扇部分和燃气涡轮发动机。

    BOSS FOR COMBUSTOR PANEL
    8.
    发明申请
    BOSS FOR COMBUSTOR PANEL 审中-公开

    公开(公告)号：WO2015038259A1

    公开(公告)日：2015-03-19

    申请号：PCT/US2014/049845

    申请日：2014-08-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BOULDIN, Lee Edward ,  PACHECO-TOUGAS, Monica ,  MOURA, Dennis M. ,  EASTWOOD, Jonathan Jeffery

    IPC: F23R3/42 ,  F23R3/60 ,  F02C7/20

    CPC classification number: F23M5/085 ,  F23R3/002 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.

    Abstract translation: 用于燃气涡轮发动机的燃烧器具有燃烧器外壳。 面板具有面向热的燃烧产物的内表面和围绕特征的凸台，凸台延伸到外端。 间隔表面与凸台间隔开，并且处于位于凸台的外端内侧的外部位置。 间隔表面将面板与外壳隔开。 槽位于凸台和间隔表面之间。 槽延伸到位于间隔表面的外部位置的内侧的外端。 还公开了一种燃气涡轮发动机。

    GAS TURBINE ENGINE CORE UTILIZED IN BOTH COMMERCIAL AND MILITARY ENGINES
    10.
    发明申请
    GAS TURBINE ENGINE CORE UTILIZED IN BOTH COMMERCIAL AND MILITARY ENGINES 审中-公开
    在两个商业和军事发动机中使用的气体涡轮发动机核心

    公开(公告)号：WO2014130494A1

    公开(公告)日：2014-08-28

    申请号：PCT/US2014/017015

    申请日：2014-02-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROBERGE, Gary D. ,  CARLTON, Richard A. ,  HUDSON, Eric A.

    IPC: F02K3/072 ,  F02K3/04 ,  F02C7/00

    CPC classification number: F02C3/073 ,  F02C3/107 ,  F02C3/14 ,  F02C7/24 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2230/52 ,  F05D2230/60 ,  Y10T29/49236

    Abstract: A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed.

    Abstract translation: 一种制造军用发动机的方法包括以下步骤：设计包括燃烧器，由高压汽轮机驱动的高压压缩机和设计成驱动低压压缩机的低压涡轮机的商业发动机芯，以及风扇通过 齿轮减速。 将高速风扇连接到低压涡轮机，使得用于商业目的的发动机的燃烧器，高压压缩机，低压和高压涡轮机用于军事目的。 还公开了一种燃气涡轮发动机。

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