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    Turbine vane gusset
    11.
    发明授权
    Turbine vane gusset 有权

    公开(公告)号：US10301951B2

    公开(公告)日：2019-05-28

    申请号：US15160216

    申请日：2016-05-20

    Applicant: United Technologies Corporation

    Inventor： Russell J. Bergman ,  Jeffrey Michael Jacques ,  Daniel Belotto

    IPC: F01D9/02 ,  F01D11/00 ,  F01D25/24 ,  F02C3/04

    Abstract: A turbine vane for a gas turbine engine includes an outer platform including a first side spaced circumferentially apart from a second side, a forward end and an aft end. The first side includes a first gusset extending between the forward end and the aft end. The first gusset defines a first radius beginning at the forward end that transitions into an elliptical curve toward the aft end. An inner platform is also included. An airfoil extends between the outer platform and the inner platform. A gas turbine engine is also disclosed.

    Platforms with leading edge features
    13.
    发明授权
    Platforms with leading edge features 有权

    公开(公告)号：US10132182B2

    公开(公告)日：2018-11-20

    申请号：US14937360

    申请日：2015-11-10

    Applicant: United Technologies Corporation

    Inventor： Andrew J. Aggarwala ,  Russell J. Bergman

    IPC: F01D9/02 ,  F01D11/04 ,  F01D11/00

    Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.

    Turbine airfoil segment having film cooling hole arrangement
    14.
    发明授权
    Turbine airfoil segment having film cooling hole arrangement 有权

    公开(公告)号：US10107140B2

    公开(公告)日：2018-10-23

    申请号：US14957686

    申请日：2015-12-03

    Applicant: United Technologies Corporation

    Inventor： Mohammed Ennacer ,  Russell J. Bergman ,  Jason B. Moran

    IPC: F01D25/12 ,  F01D9/04 ,  F01D9/06 ,  F01D5/18

    Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. The airfoil includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in one of Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

    Multiple Injector Holes for Gas Turbine Engine Vane
    20.
    发明申请
    Multiple Injector Holes for Gas Turbine Engine Vane 审中-公开
    燃气轮机发动机叶片的多个进样孔

    公开(公告)号：US20160312631A1

    公开(公告)日：2016-10-27

    申请号：US15103561

    申请日：2014-11-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Russell J. Bergman ,  Charles C. Wu ,  Brett Alan Bartling

    IPC: F01D9/06 ,  F01D25/12 ,  F01D9/04 ,  F01D11/04 ,  F01D11/00

    CPC classification number: F01D9/06 ,  F01D9/041 ,  F01D11/001 ,  F01D11/04 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/81

    Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

    Abstract translation: 叶片包括从径向外部平台延伸到径向内部平台的翼型件。 一对腿从径向内部平台径向向内延伸，并且空气流动通道穿过径向外部平台延伸通过翼型件，并进入限定在该对腿部之间的腔室中。 一对腿中的一个包括多个喷射器孔，其构造成允许来自径向外平台的空气通过孔的外部。 还公开了一种燃气涡轮发动机。

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