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    GAS TURBINE ENGINE HAVING A TURBINE ROTOR WITH TORQUE TRANSFER AND BALANCE FEATURES
    42.
    发明公开
    GAS TURBINE ENGINE HAVING A TURBINE ROTOR WITH TORQUE TRANSFER AND BALANCE FEATURES 审中-公开
    燃气轮机发动机具有转矩传递和平衡特性的涡轮转子

    公开(公告)号：EP3266981A1

    公开(公告)日：2018-01-10

    申请号：EP17177510.9

    申请日：2017-06-22

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  PARTYKA, Julian ,  HUMMEL, Raymond S.

    IPC: F01D5/02 ,  F01D5/06 ,  F01D11/00 ,  F01D5/08

    Abstract: A rotor disc assembly (50) includes a rotor disc (52) and a minidisc (54). The rotor disc has a first extension member (62), a first finger (80), and a second finger (82). The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion (240) and a second portion (242) that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger (122) that radially extends from a minidisc body (120) and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove (150).

    Abstract translation: 转子盘组件（50）包括转子盘（52）和小型盘（54）。 转子盘具有第一延伸构件（62），第一指状件（80）和第二指状件（82）。 第一延伸构件从围绕轴线布置的盘体轴向延伸。 第一指状物从第一延伸构件轴向延伸。 第二指状物与第一指状物周向间隔开。 第二指状物从第一延伸构件轴向延伸。 第一手指和第二手指中的每一个都具有第一部分（240）和从第一部分的远端径向延伸的第二部分（242）。 小型磁盘可操作地连接到转子盘。 该微型盘具有从微型盘体（120）径向延伸并设置在第一手指和第二手指之间的互锁指状物（122）。 互锁指状物，第一部分和第二部分限定环槽（150）。

    CURVIC SEAL FITTING AND BALANCE WEIGHT LOCATIONS
    44.
    发明公开
    CURVIC SEAL FITTING AND BALANCE WEIGHT LOCATIONS 审中-公开
    曲线密封配合和平衡重量位置

    公开(公告)号：EP3246516A1

    公开(公告)日：2017-11-22

    申请号：EP17171600.4

    申请日：2017-05-17

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  MARIANO, Thomas A.

    IPC: F01D5/02 ,  F01D11/00

    Abstract: Aspects of the disclosure are directed to a seal (304) comprising a first fitting (320) configured to couple to a first disk (316), and a curvic joint (308) including curvic teeth, where a first distance (320a) between the first fitting (320) and the curvic teeth is equal to or greater than a first thickness (316a) of the first disk (316).

    Abstract translation: 本公开的多个方面涉及一种密封件（304），该密封件包括被配置为联接到第一盘（316）的第一配件（320）和包括弯曲齿的弯头接头（308），其中第一距离（320a） 第一配件（320），并且所述弯曲齿等于或大于所述第一盘（316）的第一厚度（316a）。

    TURBINE DISC INTERSTAGE COUPLING WITH RETENTION RING FEATURES
    45.
    发明公开
    TURBINE DISC INTERSTAGE COUPLING WITH RETENTION RING FEATURES 审中-公开
    带有保持环特征的涡轮盘式INTERSTAGE耦合

    公开(公告)号：EP3219910A1

    公开(公告)日：2017-09-20

    申请号：EP17161198.1

    申请日：2017-03-15

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  OREN, Nicholas Waters

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

    CPC classification number: F01D9/02 ,  F01D5/02 ,  F01D5/026 ,  F01D5/066 ,  F01D5/3015 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/30

    Abstract: A disc of a gas turbine engine (10) system is provided. The disc includes a disc hub (203; 403; 603) including, an interstage coupling (207; 307; 407; 607) disposed on an axially extending surface (212; 312; 412; 612) at a peripheral edge of the disc hub that includes a protrusion that extends axially beyond an outer surface of the disc hub, and a groove (233; 333; 533; 633) formed on the axially extending surface of the disc hub wherein an aft surface (216; 316; 416; 516; 616) of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface (213; 313; 413; 513; 613) that extends radially into the disc hub to a groove floor (214; 314; 414; 514; 614) that is cut into the disc hub and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc hub, and a disc web (202; 602) that extends radially outward from the disc hub, relative to an axis of rotation of the gas turbine engine.

    Abstract translation: 燃气涡轮发动机（10）系统的盘片被提供。 所述盘包括盘毂（203; 403; 603），所述盘毂包括设置在所述盘毂的外围边缘处的轴向延伸表面（212; 312; 412; 612）上的级间联接件（207; 307; 407; 607） 其包括轴向延伸超过所述盘毂的外表面的突起和形成在所述盘毂的所述轴向延伸表面上的凹槽（233; 333; 533; 633），其中后表面（216; 316; 416; 516 ;所述凹槽还包括沿径向延伸到所述盘毂中的前表面（213; 313; 413; 513; 613），所述前表面（213; 313; 413; 513; 613） 其被切入所述盘毂并且轴向延伸至径向向外延伸至所述盘毂的所述轴向延伸表面的后表面;以及盘片腹板（202; 602），其从所述盘毂的径向外侧 盘毂相对于燃气涡轮发动机的旋转轴线旋转。

    SEAL SUPPORT STRUCTURES FOR TURBOMACHINES
    46.
    发明公开
    SEAL SUPPORT STRUCTURES FOR TURBOMACHINES 审中-公开
    用于涡轮机的密封支撑结构

    公开(公告)号：EP3073060A1

    公开(公告)日：2016-09-28

    申请号：EP16160942.5

    申请日：2016-03-17

    Applicant: United Technologies Corporation

    Inventor： MAX, Seth A. ,  CHEROLIS, Anthony P. ,  PORTER, Steven D. ,  WINN, Joshua Daniel ,  REINHARDT, Gregory E. ,  LIENAU, Jeffrey J.

    IPC: F01D11/00 ,  F01D25/24

    CPC classification number: F01D25/28 ,  F01D11/003 ,  F01D11/006 ,  F01D25/24 ,  F01D25/243 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2240/60 ,  F05D2260/97

    Abstract: A seal support structure (200) for a turbomachine includes a mounting portion (201) shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion (203) disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange (205). The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

    Abstract translation: 用于涡轮机械的密封件支撑结构（200）包括成形为安装到涡轮机械的静止结构的安装部分（201）和设置在安装部分上的圆柱形腿部分（203），所述安装部分从安装部分轴向延伸。 圆柱形腿部可以包括径向延伸的凸缘（205）。 凸缘可以从圆柱形腿部的端部以90度的角度延伸。 凸缘可以至少部分地沿轴向方向延伸。 圆柱形腿部可以与安装部一体地形成。 在实施例中，圆柱形腿部不与安装部分成一体，即，圆柱形腿部是与安装部分连接的单独件。

    FLANGE TRAPPED SEAL CONFIGURATION
    47.
    发明公开
    FLANGE TRAPPED SEAL CONFIGURATION 有权
    麻省理工学院EINGESCHLOSSENE DICHTUNGSANORDNUNG

    公开(公告)号：EP3048268A1

    公开(公告)日：2016-07-27

    申请号：EP16152275.0

    申请日：2016-01-21

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  LEMOINE, Jonathan ,  ZACCHERA, Kevin

    IPC: F01D25/12 ,  F01D25/16

    CPC classification number: F01D11/005 ,  F01D25/125 ,  F01D25/162 ,  F02C3/10 ,  Y02T50/675

    Abstract: According to one embodiment of the present invention, a sealing arrangement 72 includes a turbine static structure with an inner case 60 and a seal ring 62 each having contact surfaces. The sealing arrangement 72 also has a bearing compartment 56 with a contact surface. A piston seal 74 is positioned between the inner case 60, the seal ring 62, and the bearing compartment 56 and is configured to contact the contact surfaces.

    Abstract translation: 根据本发明的一个实施例，密封装置72包括具有内壳体60和密封环62的涡轮机静态结构，每一个具有接触表面。 密封装置72还具有带有接触表面的轴承室56。 活塞密封件74位于内壳体60，密封环62和轴承隔室56之间，并且构造成与接触表面接触。

    TURBINE VANE WITH PLATFORM PAD
    48.
    发明公开
    TURBINE VANE WITH PLATFORM PAD 审中-公开
    涡轮叶片与平台垫

    公开(公告)号：EP3011141A1

    公开(公告)日：2016-04-27

    申请号：EP14813485.1

    申请日：2014-05-21

    Applicant: United Technologies Corporation

    Inventor： OLS, John T. ,  ALLEN, Richard N. ,  PORTER, Steven D. ,  SANCHEZ, Paul K. ,  PINERO, Sandra S.

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

    Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 叶片具有在径向外部平台和径向内部平台之间延伸的翼型。 至少一个平台具有名义上径向较薄的部分，以及限定径向较厚部分的垫。 垫的径向厚度大于标称的径向较薄部分的厚度。 垫在径向外平台的一侧围绕翼型的外周。 垫具有不同的径向厚度。 还公开了中间涡轮机框架和燃气涡轮发动机。

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