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    PLATFORM FOR AN AIRFOIL HAVING BOWED SIDEWALLS
    1.
    发明申请
    PLATFORM FOR AN AIRFOIL HAVING BOWED SIDEWALLS 审中-公开

    公开(公告)号：US20170145829A1

    公开(公告)日：2017-05-25

    申请号：US14948624

    申请日：2015-11-23

    Applicant: United Technologies Corporation

    Inventor： Royce E. Tatton

    IPC: F01D5/14 ,  F01D5/30 ,  F01D5/02

    Abstract: A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, a connector configured to receive a pin and secure the platform to a rotor of the gas turbine engine, and a sidewall extending from the top wall to the connector, the sidewall having a first arm and a second arm, wherein the first arm and the second arm are curved such at a bowed sidewall extends from the top wall to the connector.

    Platform for an airfoil having bowed sidewalls
    2.
    发明授权
    Platform for an airfoil having bowed sidewalls 有权

    公开(公告)号：US10584592B2

    公开(公告)日：2020-03-10

    申请号：US14948624

    申请日：2015-11-23

    Applicant: United Technologies Corporation

    Inventor： Royce E. Tatton

    IPC: F01D5/14 ,  F01D11/00 ,  F01D5/02 ,  F01D5/30

    Abstract: A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, a connector configured to receive a pin and secure the platform to a rotor of the gas turbine engine, and a sidewall extending from the top wall to the connector, the sidewall having a first arm and a second arm, wherein the first arm and the second arm are curved such at a bowed sidewall extends from the top wall to the connector.

    Fan Blade Root Integrated Sealing Solution
    4.
    发明申请
    Fan Blade Root Integrated Sealing Solution 审中-公开
    风扇叶根集成密封解决方案

    公开(公告)号：US20150104315A1

    公开(公告)日：2015-04-16

    申请号：US14401004

    申请日：2014-02-13

    Applicant: United Technologies Corporation

    Inventor： Royce E. Tatton

    IPC: F01D11/00 ,  F01D5/30

    CPC classification number: F01D11/008 ,  F01D5/3007 ,  F01D5/3053 ,  F01D11/006 ,  F04D29/083 ,  F04D29/322 ,  F05D2220/36 ,  F05D2240/80 ,  Y02T50/673

    Abstract: A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

    Abstract translation: 公开了一种燃气涡轮发动机，燃气轮机的风扇部和燃气轮机的风扇部的组装方法。 风扇部分可以包括具有狭槽的风扇轮毂，具有cast形旋转器密封件的旋转器，包括从根部延伸到尖端的翼型的风扇叶片，其中所述翼型件具有前缘并且所述根部被容纳在所述槽中， 以及安装在风扇轮毂上且布置在相邻风扇叶片之间的平台。 风扇部分还可以包括翼片密封件，其具有固定到平台侧面的基部，以及与基部一体并且从基部延伸并且朝向根部倾斜并与叶片接合的翼片，密封件从 机翼。

    GAS TURBINE ENGINE FAN BLADE PLATFORM SEAL
    8.
    发明申请
    GAS TURBINE ENGINE FAN BLADE PLATFORM SEAL 审中-公开
    气体涡轮发动机风扇叶片平台密封

    公开(公告)号：US20140169979A1

    公开(公告)日：2014-06-19

    申请号：US13715388

    申请日：2012-12-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Andrew G. Alarcon ,  Royce E. Tatton

    IPC: F01D5/14

    CPC classification number: F01D11/008 ,  F01D5/3007 ,  F05D2220/36 ,  F05D2250/75 ,  F05D2300/437 ,  Y02T50/673

    Abstract: A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.

    Abstract translation: 用于燃气涡轮发动机的风扇部分包括具有具有外表面的翼型的风扇叶片。 平台密封件粘附在翼型件上。 用于燃气涡轮发动机的风扇部分包括具有槽的风扇毂。 风扇叶片包括从根部延伸到尖端的翼型件。 根被收到在插槽中。 平台被固定到风扇轮毂并且布置在相邻的风扇叶片之间。 密封件具有固定到风扇叶片的相对侧的基部和与基部一体并且从基部延伸并且朝向根部倾斜并与平台接合以提供密封的内部流动路径的翼片。

    Airfoil platform having dual pin apertures and a vertical stiffener
    9.
    发明授权
    Airfoil platform having dual pin apertures and a vertical stiffener 有权

    公开(公告)号：US10215046B2

    公开(公告)日：2019-02-26

    申请号：US14948638

    申请日：2015-11-23

    Applicant: United Technologies Corporation

    Inventor： Royce E. Tatton

    IPC: F01D5/32 ,  F01D11/00 ,  F01D5/30

    Abstract: A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, two sidewalls extending downward from the top wall a connector attached to and connecting the two sidewalls, wherein the top wall, the sidewalls, and the connector define an interior volume of the platform, and a single stiffener extending from the connector to the top wall within the interior volume between the two sidewalls. The connector defines two parallel apertures passing through the connector.

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