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    AIRFOIL WITH TRAILING EDGE ROUNDING
    2.
    发明公开
    AIRFOIL WITH TRAILING EDGE ROUNDING 审中-公开

    公开(公告)号：EP3599346A1

    公开(公告)日：2020-01-29

    申请号：EP19188207.5

    申请日：2019-07-24

    申请人： United Technologies Corporation

    发明人： BANKS, Anton G. ,  BARRON, Alan C.

    IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D5/28

    摘要： An airfoil (60) for a gas turbine engine (20) includes a substrate portion (76) extending from an airfoil leading edge (64) to an airfoil trailing edge portion (66). The airfoil trailing edge portion includes a flared portion (82) wherein a substrate portion thickness increases along a camber line (80) of the airfoil, and a trailing edge defined as a full constant radius (84) extending from a pressure side (68) of the airfoil to a suction side (70) of the airfoil. A coating portion (78) includes a coating applied over at least a portion of the substrate portion.

    MODULATED COMBUSTOR BYPASS AND COMBUSTOR BYPASS VALVE
    3.
    发明公开
    MODULATED COMBUSTOR BYPASS AND COMBUSTOR BYPASS VALVE 审中-公开

    公开(公告)号：EP3508790A1

    公开(公告)日：2019-07-10

    申请号：EP19150786.2

    申请日：2019-01-08

    申请人： United Technologies Corporation

    发明人： BANKS, Anton G. ,  KRAMER, Stephen K.

    IPC分类号： F23R3/26 ,  F01D17/14 ,  F02C9/18

    摘要： A combustor section (26) of a gas turbine engine (20) includes a combustor (56) having a combustor inlet (62), and a combustor bypass passage (64) having a passage inlet (66) located upstream of the combustor inlet, the combustor bypass passage configured to divert a selected bypass airflow (70) around the combustor. A combustor bypass valve (72) is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. The combustor bypass valve including a valve element (80) configured to rotate about an engine central longitudinal axis (A) to move one or more valve openings (82) relative to one or more bypass passage openings (67).

    Modulated combustor bypass
    6.
    发明公开
    Modulated combustor bypass 审中-公开

    公开(公告)号：EP3470656A1

    公开(公告)日：2019-04-17

    申请号：EP18200260.0

    申请日：2018-10-12

    申请人： United Technologies Corporation

    发明人： BANKS, Anton G. ,  PROPHETER-HINCKLEY, Tracy A.

    IPC分类号： F02K3/02 ,  F02C9/18 ,  F23R3/02 ,  F23R3/26

    摘要： A combustor section (26) of a gas turbine engine (20) includes a combustor (56) having a combustor inlet (62), and a combustor bypass passage (64) having a passage inlet (66) located upstream of the combustor inlet. The combustor bypass passage is configured to divert a selected bypass airflow (70) around the combustor. A combustor bypass valve (72) is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. A method of operating a gas turbine engine (20), includes urging a core airflow from a compressor section (24) toward a combustor section (26), flowing a first portion of the core airflow into the combustor section via a combustor inlet (62), and flowing a second portion of the core airflow into a combustor bypass passage (64) via a combustor bypass valve (72), thereby bypassing the combustor with the second portion of the core airflow.

    RIM SEAL FOR GAS TURBINE ENGINE
    7.
    发明公开
    RIM SEAL FOR GAS TURBINE ENGINE 审中-公开
    用于燃气轮机的RIM密封件

    公开(公告)号：EP3287605A1

    公开(公告)日：2018-02-28

    申请号：EP17177520.8

    申请日：2017-06-22

    申请人： United Technologies Corporation

    发明人： BANKS, Anton G. ,  CORCORAN, Christopher ,  DUBE, Bryan P.

    IPC分类号： F01D11/00 ,  F01D5/02 ,  F01D5/30 ,  F01D5/08 ,  F02C7/28

    CPC分类号： F01D11/006 ,  F01D5/02 ,  F01D5/08 ,  F01D5/088 ,  F01D5/30 ,  F01D11/00 ,  F01D11/005 ,  F02C3/04 ,  F02C7/28 ,  F04D29/083 ,  F04D29/322 ,  F05D2220/323 ,  F05D2240/35 ,  Y02T50/676

    摘要： A rim seal (70) for a rotor (48; 90) of a gas turbine engine (10) includes a seal portion (74) extending circumferentially across a rim cavity (68) of a rotor, the seal portion configured to seal the rim cavity and a first foot portion (76) extending radially inwardly from a first end (78) of the seal portion. A rotor assembly for a gas turbine engine includes a rotor disc (50; 94) and a plurality of rotor blades (52; 92) secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion (66) of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the seal portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end (78) of the rim seal and from a second end (78) opposite the first end.

    摘要翻译： 用于燃气涡轮发动机（10）的转子（48; 90）的轮辋密封件（70）包括密封部分（74），该密封部分（74）横跨转子的轮辋腔体（68）周向延伸，该密封部分构造成密封轮辋 腔和从密封部分的第一端（78）径向向内延伸的第一脚部（76）。 用于燃气涡轮发动机的转子组件包括转子盘（50; 94）和固定到转子盘的多个转子叶片（52; 92），限定转子盘和转子盘的边缘部分（66）之间的边缘腔， 多个转子叶片。 轮辋密封件位于轮辋腔体中并且包括密封部分，该密封部分横跨轮辋腔体周向地延伸，该密封部分构造成密封轮辋腔体。 密封部分随着距轮辋密封件的第一端部（78）和与第一端部相对的第二端部（78）的距离增加而具有增加的径向厚度。