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    Mid-turbine frame thermal radiation shield
    6.
    发明授权
    Mid-turbine frame thermal radiation shield 有权
    中涡轮机架热辐射屏蔽

    公开(公告)号：US09303528B2

    公开(公告)日：2016-04-05

    申请号：US13543243

    申请日：2012-07-06

    申请人： Paul K. Sanchez ,  Jorge I. Farah

    发明人： Paul K. Sanchez ,  Jorge I. Farah

    IPC分类号： F01D25/28 ,  F01D25/16 ,  F01D9/06 ,  F01D25/14

    CPC分类号： F01D25/162 ,  F01D9/065 ,  F01D25/145 ,  F01D25/28 ,  F05D2230/54 ,  F05D2240/15 ,  Y02T50/675

    摘要： A thermal radiation shield comprises a first mounting base and a ring section. The first mounting base is disposed at a first axial end of the ring section for securing the shield ring section within a generally annular cavity defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.

    摘要翻译： 热辐射屏蔽包括第一安装基座和环形部分。 第一安装基座设置在环形部分的第一轴向端部处，用于将屏蔽环部分固定在至少部分由热流体流路边界壁限定的大致环形空腔内，以及径向相邻且间隔开的冷流体流 路边界。 环部被配置为基本上阻挡热流体流路边界壁和冷流体流路边界壁之间的视线。

    MID-TURBINE FRAME THERMAL RADIATION SHIELD
    7.
    发明申请
    MID-TURBINE FRAME THERMAL RADIATION SHIELD 有权
    中涡轮架热辐射屏蔽

    公开(公告)号：US20140007588A1

    公开(公告)日：2014-01-09

    申请号：US13543243

    申请日：2012-07-06

    申请人： Paul K. Sanchez ,  Jorge I. Farah

    发明人： Paul K. Sanchez ,  Jorge I. Farah

    IPC分类号： F02C7/20 ,  F28F13/00

    CPC分类号： F01D25/162 ,  F01D9/065 ,  F01D25/145 ,  F01D25/28 ,  F05D2230/54 ,  F05D2240/15 ,  Y02T50/675

    摘要： A thermal radiation shield comprises a first mounting base and a ring section. The first mounting base is disposed at a first axial end of the ring section for securing the shield ring section within a generally annular cavity defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.

    摘要翻译： 热辐射屏蔽包括第一安装基座和环形部分。 第一安装基座设置在环形部分的第一轴向端部处，用于将屏蔽环部分固定在至少部分由热流体流路边界壁限定的大致环形空腔内，以及径向相邻且间隔开的冷流体流 路边界。 环部被配置为基本上阻挡热流体流路边界壁和冷流体流路边界壁之间的视线。

    Dual-Intent Locator Pin and Removable Plug for Gas Turbines
    8.
    发明申请
    Dual-Intent Locator Pin and Removable Plug for Gas Turbines 有权
    燃气轮机的双重定位销和可拆卸插头

    公开(公告)号：US20130259646A1

    公开(公告)日：2013-10-03

    申请号：US13431041

    申请日：2012-03-27

    申请人： David T. Feindel ,  Jorge I. Farah

    发明人： David T. Feindel ,  Jorge I. Farah

    IPC分类号： F02C7/00 ,  B23P17/00

    CPC分类号： F01D25/246 ,  F01D21/003 ,  F05D2260/403 ,  F05D2260/80 ,  Y10T29/49229

    摘要： A borescope plug configuration is disclosed. The borescope plug configuration comprises an inspection path defined through a bore in a first engine structure, a second engine structure, and an opening into the gas path of an engine. The borescope plug configuration further comprises a removable plug for sealing the inspection path. The removable plug is adapted to couple the first engine structure to the second engine structure.

    摘要翻译： 公开了管道镜插头配置。 管孔塞塞构造包括通过第一发动机结构中的孔，第二发动机结构和通向发动机的气体通道的开口限定的检查路径。 管孔塞插头配置还包括用于密封检查路径的可移除插头。 可拆卸插头适于将第一发动机结构联接到第二发动机结构。

    AIRFOIL ATTACHMENT ARRANGEMENT
    9.
    发明申请
    AIRFOIL ATTACHMENT ARRANGEMENT 有权
    飞机附件安排

    公开(公告)号：US20120107124A1

    公开(公告)日：2012-05-03

    申请号：US12915575

    申请日：2010-10-29

    申请人： Jorge I. Farah ,  Jaisukhlal V. Chokshi

    发明人： Jorge I. Farah ,  Jaisukhlal V. Chokshi

    IPC分类号： F01D5/30

    CPC分类号： F01D9/042

    摘要： An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.

    摘要翻译： 示例性翼型保持装置包括具有第一保持段和第二保留段的保持组件。 每个保持段分别可移动到相对于翼型组件和支撑结构的安装位置。 当保持段处于安装位置时，保持段各自具有在翼型组件的唇缘和支撑结构的套环之间的部分位置。 保持组件构造成在处于安装位置时限制翼型件相对于支撑结构的径向移动。

    Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct
    10.
    发明授权
    Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct 有权
    用于燃气涡轮发动机旋转排气管道内的冷却衬套的薄型连接悬挂系统

    公开(公告)号：US07814753B2

    公开(公告)日：2010-10-19

    申请号：US11492412

    申请日：2006-07-25

    申请人： Jorge I. Farah ,  William G. Hoop

    发明人： Jorge I. Farah ,  William G. Hoop

    IPC分类号： F02C7/20

    CPC分类号： F02K1/822 ,  F01D25/30 ,  F05D2220/90 ,  Y02T50/671 ,  Y02T50/675 ,  Y10T29/49323

    摘要： An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up/down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections.

    摘要翻译： 排气管道组件包括与排气管道壳体间隔开的冷却衬套，所述排气管道壳体铰接用于在垂直起落架（STOVL）类型的飞行器中使用。 冷却衬套组件通过可折叠的连接悬挂系统附接到排气管道壳体。 可折叠连接衣架系统为三个轴承旋转管道（3BSD）提供了一个有限的入口安装信封，该三个轴承旋转管道（3BSD）围绕三个轴承平面旋转，以允许在巡航配置和悬停配置之间过渡。 以这种方式，每个冷却衬套段可以形成为仅在可旋转导管段之间仅需要接头的完整圆柱形构件。