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    COOLING SYSTEM FOR A TURBINE VANE
    1.
    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
    2.
    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。

    HYBRID INNER AIR SEAL FOR GAS TURBINE ENGINES
    3.
    发明申请
    HYBRID INNER AIR SEAL FOR GAS TURBINE ENGINES 有权
    用于气体涡轮发动机的混合内部空气密封

    公开(公告)号：US20130183145A1

    公开(公告)日：2013-07-18

    申请号：US13351290

    申请日：2012-01-17

    申请人： Joseph T. Caprario ,  Russell J. Bergman ,  Pamela A. Humphrey ,  Jonathan Perry Sandoval

    发明人： Joseph T. Caprario ,  Russell J. Bergman ,  Pamela A. Humphrey ,  Jonathan Perry Sandoval

    IPC分类号： F01D11/00

    CPC分类号： F01D11/001 ,  F01D9/04 ,  F01D11/025

    摘要： A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.

    摘要翻译： 涡轮部分具有承载涡轮叶片的涡轮转子。 涡轮机叶片包括在径向内部位置处的密封构件。 叶片部分由多个周向间隔开的叶片部件形成，每个叶片部件具有从平台径向向外延伸的翼型件。 第一密封构件固定到平台上，并且被定位成与相对于第一密封构件沿一个轴向方向定位的叶片相邻的密封件。 第二密封构件周向地延伸超过至少多个叶片部件，并且定位成在与第一叶片相对的轴向侧上与叶片的密封构件相邻。 还公开并要求保护叶片部件。

    Hybrid inner air seal for gas turbine engines
    4.
    发明授权
    Hybrid inner air seal for gas turbine engines 有权
    用于燃气轮机的混合内部气密封

    公开(公告)号：US09416673B2

    公开(公告)日：2016-08-16

    申请号：US13351290

    申请日：2012-01-17

    申请人： Joseph T. Caprario ,  Russell J. Bergman ,  Pamela A. Humphrey ,  Jonathan Perry Sandoval

    发明人： Joseph T. Caprario ,  Russell J. Bergman ,  Pamela A. Humphrey ,  Jonathan Perry Sandoval

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

    CPC分类号： F01D11/001 ,  F01D9/04 ,  F01D11/025

    摘要： A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.

    摘要翻译： 涡轮部分具有承载涡轮叶片的涡轮转子。 涡轮机叶片包括在径向内部位置处的密封构件。 叶片部分由多个周向间隔开的叶片部件形成，每个叶片部件具有从平台径向向外延伸的翼型件。 第一密封构件固定到平台上，并且被定位成与相对于第一密封构件沿一个轴向方向定位的叶片相邻的密封件。 第二密封构件周向地延伸超过至少多个叶片部件，并且定位成在与第一叶片相对的轴向侧上与叶片的密封构件相邻。 还公开并要求保护叶片部件。

    GAS TURBINE SYSTEMS INVOLVING ROTOR BAYONET COVERPLATES AND TOOLS FOR INSTALLING SUCH COVERPLATES
    5.
    发明申请
    GAS TURBINE SYSTEMS INVOLVING ROTOR BAYONET COVERPLATES AND TOOLS FOR INSTALLING SUCH COVERPLATES 有权
    涉及用于安装这种覆盖物的转子BAYONET COVERPLATES和工具的气体涡轮机系统

    公开(公告)号：US20120311835A1

    公开(公告)日：2012-12-13

    申请号：US13544668

    申请日：2012-07-09

    申请人： Joseph T. Caprario ,  Daniel J. Griffin

    发明人： Joseph T. Caprario ,  Daniel J. Griffin

    IPC分类号： B23P19/04

    CPC分类号： F01D5/3015 ,  F05D2260/33 ,  Y10T29/37 ,  Y10T29/4932 ,  Y10T29/49945 ,  Y10T29/53 ,  Y10T29/53657 ,  Y10T29/53678 ,  Y10T29/53909 ,  Y10T29/53961

    摘要： Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

    摘要翻译： 提供涉及转子卡口盖板的燃气涡轮发动机系统和用于安装这种盖板的工具。 在这方面，用于燃气涡轮发动机的代表性的涡轮组件包括：涡轮盘，其可操作地安装一组涡轮叶片; 以及具有环形主体部分和间隔开的从所述主体部分径向向内延伸的环形布置的盖板，其中开口间隙位于所述突片之间，所述突出部可操作以将所述盖板的内径固定到所述涡轮机 磁盘。

    Rotor cover plate retention method
    7.
    发明授权
    Rotor cover plate retention method 有权
    转子盖板固定方法

    公开(公告)号：US08870544B2

    公开(公告)日：2014-10-28

    申请号：US12846304

    申请日：2010-07-29

    申请人： Joseph T. Caprario

    发明人： Joseph T. Caprario

    IPC分类号： F01D5/00 ,  F01D5/08

    CPC分类号： F01D5/082 ,  F01D5/066 ,  F05D2260/30 ,  F05D2260/33

    摘要： A mechanism for use in a gas turbine engine has a cover plate, a rotor disk, a first slot in the cover plate, a second slot in the rotor disk, a first finger in the cover plate extending through the second slot, and a second finger in the rotor disk extending through the first slot. The first finger and the second finger form a channel and a holder is disposed in the channel for locking the rotor disk and the cover plate together.

    摘要翻译： 用于燃气涡轮发动机的机构具有盖板，转子盘，盖板中的第一槽，转子盘中的第二槽，延伸穿过第二槽的盖板中的第一手指，以及第二槽 转子盘中的手指延伸穿过第一槽。 第一指状物和第二指状物形成通道，并且保持器设置在通道中用于将转子盘和盖板锁定在一起。

    Gas Turbine Engine Systems Involving Rotor Bayonet Coverplates and Tools for Installing Such Coverplates
    9.
    发明申请
    Gas Turbine Engine Systems Involving Rotor Bayonet Coverplates and Tools for Installing Such Coverplates 有权
    涉及用于安装这种盖板的转子卡口盖板和工具的燃气轮机发动机系统

    公开(公告)号：US20090148295A1

    公开(公告)日：2009-06-11

    申请号：US11952367

    申请日：2007-12-07

    申请人： Joseph T. Caprario ,  Daniel J. Griffin

    发明人： Joseph T. Caprario ,  Daniel J. Griffin

    IPC分类号： F01D1/02

    CPC分类号： F01D5/3015 ,  F05D2260/33 ,  Y10T29/37 ,  Y10T29/4932 ,  Y10T29/49945 ,  Y10T29/53 ,  Y10T29/53657 ,  Y10T29/53678 ,  Y10T29/53909 ,  Y10T29/53961

    摘要： Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

    摘要翻译： 提供涉及转子卡口盖板的燃气涡轮发动机系统和用于安装这种盖板的工具。 在这方面，用于燃气涡轮发动机的代表性的涡轮组件包括：涡轮盘，其可操作地安装一组涡轮叶片; 以及具有环形主体部分和间隔开的从所述主体部分径向向内延伸的环形布置的盖板，其中开口间隙位于所述突片之间，所述突出部可操作以将所述盖板的内径固定到所述涡轮机 磁盘。