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    Airfoil with variable trip strip height
    12.
    发明授权
    Airfoil with variable trip strip height 有权
    具有可变跳闸带高度的翼型

    公开(公告)号：US09334755B2

    公开(公告)日：2016-05-10

    申请号：US13630107

    申请日：2012-09-28

    Applicant: United Technologies Corporation

    Inventor： Sarah Riley ,  Mark A. Boeke ,  Jeffrey J. DeGray ,  Shawn J. Gregg

    IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2250/183 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。

    Low loss airfoil platform rim seal assembly
    13.
    发明授权
    Low loss airfoil platform rim seal assembly 有权

    公开(公告)号：US10648353B2

    公开(公告)日：2020-05-12

    申请号：US14942484

    申请日：2015-11-16

    Applicant: United Technologies Corporation

    Inventor： Andrew S. Aggarwala ,  Russell J. Bergman ,  Mark A. Boeke ,  Kyle C. Lana ,  Daniel A. Snyder

    IPC: F01D11/02 ,  F01D11/00 ,  F01D5/22

    Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.

    AIRFOIL COOLING PASSAGE
    15.
    发明申请
    AIRFOIL COOLING PASSAGE 审中-公开
    AIRFOIL冷却通道

    公开(公告)号：US20160326894A1

    公开(公告)日：2016-11-10

    申请号：US14706518

    申请日：2015-05-07

    Applicant: United Technologies Corporation

    Inventor： Mark A. Boeke ,  Jeffrey J. DeGray ,  Richard M. Salzillo

    IPC: F01D9/04 ,  F01D25/12

    CPC classification number: F01D9/041 ,  F01D25/12 ,  F05D2240/81 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes a first platform located at a first end of a first airfoil. A cooling passage extends through the first platform and includes a first portion that has a first thickness and a second portion that has a second thickness and surrounds opposing ends of the first portion.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括位于第一翼型件的第一端的第一平台。 冷却通道延伸穿过第一平台并且包括具有第一厚度的第一部分和具有第二厚度并且包围第一部分的相对端部的第二部分。

    COOLING FEED ORIFICES
    16.
    发明申请
    COOLING FEED ORIFICES 有权
    冷却饲料

    公开(公告)号：US20160208627A1

    公开(公告)日：2016-07-21

    申请号：US14599075

    申请日：2015-01-16

    Applicant: United Technologies Corporation

    Inventor： Mark A. Boeke ,  Kristopher K. Anderson ,  Jeffrey J. De Gray ,  Jeffrey R. Levine ,  Sarah Riley ,  Richard M. Salzillo, JR.

    IPC: F01D9/02

    CPC classification number: F01D25/12 ,  F01D9/023 ,  F01D9/04 ,  F01D9/06 ,  F05D2240/81 ,  Y02T50/676

    Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.

    Abstract translation: 翼型平台包括具有限定中心线轴线的弓形基部的平台本体。 轨道从弓形底座的一侧沿径向外侧延伸。 进料口至少部分地限定在轨道中。 进料孔的轴向面向的开口的内径边缘在弧形底座的外径表面的径向外侧间隔开。 一种用于制造翼型平台的方法包括提供翼型平台本体并通过导轨形成进料口。 通过导轨形成进料孔包括在弓形底座的外径表面径向地形成进料孔并且间隔开。

    Support Buttress
    17.
    发明申请
    Support Buttress 有权
    支撑支撑

    公开(公告)号：US20160201485A1

    公开(公告)日：2016-07-14

    申请号：US14593886

    申请日：2015-01-09

    Applicant: United Technologies Corporation

    Inventor： Mark A. Boeke ,  Richard M. Salzillo, JR. ,  Jeffrey J. Degray

    IPC: F01D9/02 ,  F01D25/28 ,  F01D9/04

    CPC classification number: F01D9/023 ,  F01D9/04 ,  F01D9/06 ,  F01D25/28 ,  F05D2240/81 ,  Y02T50/676

    Abstract: An airfoil of a turbine engine may have internal passages to permit the travel of cooling air through the airfoil. Multiple airfoils may be formed together in a stator vane assembly, and cooling air may be directed through the stator vane assembly. The stator vane assembly may be mounted to an engine structure to carry structural loads experienced by the stator vane assembly. Buttresses may be formed in the stator vane assembly, such as beneath each airfoil of the stator vane assembly, and extending into a passage permitting the travel of cooling air through the airfoil. The buttresses may enhance the strength and stability of the stator vane assembly by facilitating the transmission of structural loads to an engine structure. A channel may be defined through one or more buttress to enable the passage of cooling air into the airfoils, and yet allow the buttresses to carry structural loads.

    Abstract translation: 涡轮发动机的翼型件可以具有允许冷却空气通过翼型的行进的内部通道。 多个翼型件可以一起形成在定子叶片组件中，并且冷却空气可以被引导通过定子叶片组件。 定子叶片组件可以安装到发动机结构以承载由定子叶片组件经受的结构负载。 支撑件可以形成在定子叶片组件中，例如在定子叶片组件的每个翼型件下面，并且延伸到允许冷却空气通过翼型件的行进的通道中。 支撑件可以通过促进将结构载荷传递到发动机结构来增强定子叶片组件的强度和稳定性。 通道可以通过一个或多个支撑件来限定，以使冷却空气能够进入翼型件，并允许支撑架承载结构载荷。

    GAS TURBINE ENGINE MULTI-VANED STATOR COOLING CONFIGURATION
    18.
    发明申请
    GAS TURBINE ENGINE MULTI-VANED STATOR COOLING CONFIGURATION 审中-公开
    气体涡轮发动机多通道定子冷却配置

    公开(公告)号：US20160003152A1

    公开(公告)日：2016-01-07

    申请号：US14769224

    申请日：2014-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Sarah Riley ,  Mark A. Boeke ,  Shawn J. Gregg

    IPC: F02C7/18 ,  F01D9/04 ,  F01D25/12 ,  F02C3/04

    Abstract: A stator for a gas turbine engine has a platform supporting multiple vanes that includes first and second vanes respectively. First and second regions are arranged at the same location on the first and second vanes. The first and second regions respectively include first and second cooling hole configurations that are different than one another.

    Abstract translation: 用于燃气涡轮发动机的定子具有分别支撑包括第一和第二叶片的多个叶片的平台。 第一和第二区域布置在第一和第二叶片上的相同位置。 第一和第二区域分别包括彼此不同的第一和第二冷却孔构造。

    Cooled turbine vane with alternately orientated film cooling hole rows
    20.
    发明授权
    Cooled turbine vane with alternately orientated film cooling hole rows 有权

    公开(公告)号：US10443401B2

    公开(公告)日：2019-10-15

    申请号：US15255187

    申请日：2016-09-02

    Applicant: United Technologies Corporation

    Inventor： Nicholas M. LoRicco ,  Mark A. Boeke ,  Richard M. Salzillo, Jr. ,  Jeffrey J. DeGray

    IPC: F01D5/18 ,  F01D25/12

    Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.

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