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    BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT
    4.
    发明申请
    BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT 有权
    叶片外部空气密封组件和支撑

    公开(公告)号：US20120189426A1

    公开(公告)日：2012-07-26

    申请号：US13012845

    申请日：2011-01-25

    申请人： Anne-Marie B. Thibodeau ,  Bruce E. Chick ,  Thurman Carlo Dabbs ,  James N. Knapp ,  Dmitriy A. Romanov ,  Russell E. Keene ,  Jeffrey Vincent Anastas

    发明人： Anne-Marie B. Thibodeau ,  Bruce E. Chick ,  Thurman Carlo Dabbs ,  James N. Knapp ,  Dmitriy A. Romanov ,  Russell E. Keene ,  Jeffrey Vincent Anastas

    IPC分类号： F01D25/12 ,  F01D11/08

    CPC分类号： F01D25/246 ,  F01D11/08 ,  F01D11/125 ,  F05D2240/11 ,  F05D2260/202

    摘要： An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member. An example blade outer air seal assembly includes a blade outer air seal assembly having an inwardly facing surface. A blade path portion of the inwardly facing surface is axially aligned with a tip of a rotating blade. A peripheral portion of the inwardly facing surface is located axially in front of the blade path portion, axially behind the blade path portion, or both. The blade outer air seal assembly establishes cooling paths that terminate at a plurality of apertures established within the inwardly facing surface. The plurality of apertures are locate exclusively within the blade path portion.

    摘要翻译： 示例性的叶片外部空气密封支撑组件包括构造成支撑叶片外部空气密封件的主支撑构件。 主支撑构件在前缘部分和后缘部分之间大致轴向地延伸。 前缘部分构造成可滑动地容纳在由叶片外部空气密封件建立的凹槽内。 支撑突片从支撑构件朝向叶片外部空气密封件径向延伸。 支撑突片被构造成接触叶片外部空气密封件的延伸部以限制叶片外部空气密封件的相对轴向运动。 角撑板在支撑片和支撑构件之间跨越。 示例性的叶片外部空气密封组件包括具有向内的表面的叶片外部空气密封组件。 面向内的表面的刀片路径部分与旋转刀片的尖端轴向对准。 面向内的表面的周边部分轴向位于叶片路径部分的前面，轴向位于叶片路径部分之后，或两者。 叶片外部空气密封组件建立冷却路径，其终止于在面向内的表面内建立的多个孔。 多个孔仅位于刀片路径部分内。

    COOLING SYSTEM FOR A TURBINE VANE
    5.
    发明申请
    COOLING SYSTEM FOR A TURBINE VANE 有权
    涡轮风扇冷却系统

    公开(公告)号：US20130266416A1

    公开(公告)日：2013-10-10

    申请号：US13439277

    申请日：2012-04-04

    申请人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

    发明人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

    IPC分类号： F01D25/12 ,  F01D9/02

    CPC分类号： F01D25/246 ,  F01D25/14 ,  F05D2240/81

    摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

    摘要翻译： 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

    Cooling system for a turbine vane
    6.
    发明授权
    Cooling system for a turbine vane 有权
    涡轮叶片冷却系统

    公开(公告)号：US08961108B2

    公开(公告)日：2015-02-24

    申请号：US13439277

    申请日：2012-04-04

    申请人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

    发明人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

    IPC分类号： F01D9/06

    CPC分类号： F01D25/246 ,  F01D25/14 ,  F05D2240/81

    摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

    摘要翻译： 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

    Blade outer air seal for a gas turbine engine
    7.
    发明授权
    Blade outer air seal for a gas turbine engine 有权
    用于燃气涡轮发动机的叶片外部空气密封

    公开(公告)号：US08998572B2

    公开(公告)日：2015-04-07

    申请号：US13487347

    申请日：2012-06-04

    申请人： Paul M. Lutjen ,  Thurman Carlo Dabbs

    发明人： Paul M. Lutjen ,  Thurman Carlo Dabbs

    IPC分类号： F01D11/12 ,  F04D29/16

    CPC分类号： F04D29/164 ,  F01D11/08 ,  F04D29/526 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

    摘要： A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

    摘要翻译： 根据本公开的示例性实施例的叶片外部空气密封（BOAS）段可以包括密封体，其具有径向内表面和径向外表面，所述径向内表面和径向外表面在第一配合面和第二配合面之间周向延伸， 前缘面和后缘面。 第一配合面，第二配合面，径向外表面和径向内表面中的至少一个可以包括具有突出部的内壁和从突出部沿径向延伸的沿着突出部的长度不间断延伸的底切通道。

    BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE
    8.
    发明申请
    BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE 有权
    用于气体涡轮发动机的叶片外部空气密封件

    公开(公告)号：US20130323032A1

    公开(公告)日：2013-12-05

    申请号：US13487347

    申请日：2012-06-04

    申请人： Paul M. Lutjen ,  Thurman Carlo Dabbs

    发明人： Paul M. Lutjen ,  Thurman Carlo Dabbs

    IPC分类号： F04D29/08

    CPC分类号： F04D29/164 ,  F01D11/08 ,  F04D29/526 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

    摘要： A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

    摘要翻译： 根据本公开的示例性实施例的叶片外部空气密封（BOAS）段可以包括密封体，其具有径向内表面和径向外表面，所述径向内表面和径向外表面在第一配合面和第二配合面之间周向延伸， 前缘面和后缘面。 第一配合面，第二配合面，径向外表面和径向内表面中的至少一个可以包括具有突出部的内壁和从突出部沿径向延伸的沿着突出部的长度不间断延伸的底切通道。

    Particle collector for gas turbine engine
    9.
    发明授权
    Particle collector for gas turbine engine 有权
    燃气轮机发动机用颗粒捕集器

    公开(公告)号：US07770375B2

    公开(公告)日：2010-08-10

    申请号：US11350494

    申请日：2006-02-09

    申请人： Ioannis Alvanos ,  Bernard A. Andrews ,  Robert A. Charbonneau ,  Susan M. Tholen ,  Thurman Carlo Dabbs ,  Michael J. Bruskotter

    发明人： Ioannis Alvanos ,  Bernard A. Andrews ,  Robert A. Charbonneau ,  Susan M. Tholen ,  Thurman Carlo Dabbs ,  Michael J. Bruskotter

    IPC分类号： F02G3/00

    CPC分类号： F01D25/32 ,  F02C7/05 ,  F05D2260/20 ,  F05D2260/607

    摘要： A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized. The material may have a surface that will sit with at least a component parallel to an axial centerline of a gas turbine engine that is to receive the collection material. The material surface may also have a component which is generally perpendicular to the axial centerline. The material may be placed in a gas turbine engine upstream of the turbine section, and downstream of the combustion section. Moreover, the collection material may be placed such that there is cleaner air flow radially inwardly of the collection material, and heavier dirt-laden air passing along the collection material such that impurities can be collected.

    摘要翻译： 具有多个杂质收集空间的材料具有面向燃气涡轮发动机部件的冷却空气流动流的外表面。 诸如沙子或污垢的杂质将聚集在多个空间中。 在公开的实施例中，使用蜂窝状材料。 该材料可以具有将至少与平行于要接收收集材料的燃气涡轮发动机的轴向中心线的部件坐落的表面。 材料表面也可以具有通常垂直于轴向中心线的部件。 该材料可以被放置在涡轮机部分上游的燃气涡轮发动机中，并且在燃烧部分的下游。 此外，收集材料可以被放置成使得收集材料的径向向内具有更清洁的空气流，并且沿着收集材料通过的较重的污垢填充空气可以收集杂质。