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    Stator vane arrangement for a turbine engine
    1.
    发明授权
    Stator vane arrangement for a turbine engine 有权

    公开(公告)号：US10344606B2

    公开(公告)日：2019-07-09

    申请号：US14779846

    申请日：2014-04-01

    申请人： United Technologies Corporation

    发明人： Jorge I. Farah ,  Conway Chuong ,  Dana P. Stewart

    IPC分类号： F01D9/04 ,  F01D25/16 ,  F01D25/00

    摘要： A stator vane arrangement for a turbine engine includes a first vane platform, a second vane platform and a plurality of stator vanes extending radially between the first and the second vane platforms. The first and the second vane platforms extend circumferentially around an axis, and the first vane platform includes an aperture. The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform.

    Assembly for sealing a gap between components of a turbine engine
    3.
    发明授权
    Assembly for sealing a gap between components of a turbine engine 有权

    公开(公告)号：US10196911B2

    公开(公告)日：2019-02-05

    申请号：US14775412

    申请日：2014-03-14

    申请人： United Technologies Corporation

    发明人： Decari S. Jenkins ,  Jorge I. Farah

    IPC分类号： F01D11/00 ,  F01D25/24 ,  F01D9/04 ,  F01D11/08

    摘要： A turbine engine assembly includes a first component, a second component and a third component arranged along an axis. The first component houses at least a portion of the third component. The assembly also includes a seal carrier, a seal land and a seal element, which seals a gap between the seal carrier and the seal land. The seal carrier is connected to the first component, and includes a groove surface and a groove. A first portion of the seal carrier seals a gap between a second portion of the seal carrier and the second component. The seal land is connected to the third component and includes a seal land surface. The seal element extends radially into the groove. The seal element is axially engaged with the groove surface and radially engaged with the seal land surface.

    GAS TURBINE ENGINE MID-TURBINE FRAME CONFIGURATION
    6.
    发明申请
    GAS TURBINE ENGINE MID-TURBINE FRAME CONFIGURATION 有权
    气体涡轮发动机中间涡轮机框架配置

    公开(公告)号：US20160245105A1

    公开(公告)日：2016-08-25

    申请号：US14629090

    申请日：2015-02-23

    申请人： United Technologies Corporation

    发明人： Jorge I. Farah ,  John T. Ols

    IPC分类号： F01D9/04 ,  F01D25/24 ,  F01D11/00

    CPC分类号： F01D9/041 ,  F01D9/042 ,  F01D9/065 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/3213 ,  F05D2230/21 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/31

    摘要： A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path. A mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

    摘要翻译： 燃气涡轮发动机包括围绕发动机轴线轴向延伸的铁心流路。 涡轮部分布置在核心流动路径中。 中间涡轮机框架包括多个周向间隔开的叶片，其在限定芯流动路径的一部分之间径向延伸并且互连内部和外部流动路径表面。 叶片和内部和外部流动路径表面由单一的一体式铸造结构提供。 内部流路表面相对于发动机轴线提供入口和出口内径。 外部流路表面相对于发动机轴线提供入口和出口外径。 内部流路表面从入口内径延伸到出口内径的轴向长度。 出口外径与轴向长度之比大于3.0比1。

    Mid-Turbine Frame with Fairing Attachment
    9.
    发明申请
    Mid-Turbine Frame with Fairing Attachment 有权
    带涡流机附件的中型涡轮机架

    公开(公告)号：US20150260057A1

    公开(公告)日：2015-09-17

    申请号：US14438562

    申请日：2013-09-11

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Jorge I. Farah ,  Jonathan P. Burt ,  Paul K. Sanchez ,  Kalpendu J. Parekh ,  Jonathan J. Jakiel

    IPC分类号： F01D25/28

    CPC分类号： F01D25/28 ,  F01D25/162 ,  F01D25/24 ,  F01D25/26 ,  F02C7/20 ,  F05D2240/91

    摘要： A mid-turbine frame (MTF) system for a gas turbine engine is disclosed. The MTF includes an inner case, an outer case and a fairing sandwiched between the inner and outer cases. The fairing includes an inner ring spaced apart from and coupled to an outer ring by a plurality of hollow struts. The hollow struts accommodate support rods that connect the inner case to the outer case. Further, the hollow struts act as turning vanes for turning the flow of gases passing from a high pressure turbine (HPT) to a low pressure turbine (LPT) for purposes of providing the correct incidence angle to the first vane of the LPT. The outer ring of the fairing includes a plurality of bosses which receive attachment pins that pass through the outer case for correctly locating the fairing with respect to the outer case and for permitting radial expansion in contraction of the fairing.

    摘要翻译： 公开了一种用于燃气涡轮发动机的中涡轮机架（MTF）系统。 MTF包括夹在内壳和外壳之间的内壳，外壳和整流罩。 整流罩包括通过多个中空支柱间隔开并与外环连接的内圈。 中空支柱适应将内壳连接到外壳的支撑杆。 此外，为了向LPT的第一叶片提供正确的入射角，中空支柱用作转动叶片，用于将从高压涡轮（HPT）通过的气体流转向低压涡轮机（LPT）。 整流罩的外圈包括多个凸台，其接收穿过外壳的连接销，以便正确地将整流罩相对于外壳定位并允许整流罩收缩的径向膨胀。