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    Gas turbine engine compressor case mounting arrangement
    45.
    发明授权
    Gas turbine engine compressor case mounting arrangement 有权
    燃气涡轮发动机压缩机壳体安装布置

    公开(公告)号：US08596965B2

    公开(公告)日：2013-12-03

    申请号：US13294492

    申请日：2011-11-11

    申请人： Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    发明人： Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC分类号： F01D1/00

    CPC分类号： F01D25/24 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/12 ,  F05D2240/55

    摘要： A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.

    摘要翻译： 用于燃气涡轮发动机的压缩机壳体支撑装置包括具有中心轴线的风扇部分和用于容纳压缩机的压缩机壳体。 入口箱将空气引导到压缩机。 压缩机壳体比入口箱更远离风扇部分。 支撑构件在风扇部分和压缩机壳体之间延伸。 支撑构件限制压缩机壳体相对于入口壳体的移动。 支撑构件比管道通路区域更远离风扇部分。

    GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT
    47.
    发明申请
    GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT 有权
    具有独立核心和推进单元的气体涡轮发动机

    公开(公告)号：US20130205752A1

    公开(公告)日：2013-08-15

    申请号：US13370750

    申请日：2012-02-10

    申请人： Gabriel L. Suciu ,  Wesley K. Lord ,  Christopher M. Dye

    发明人： Gabriel L. Suciu ,  Wesley K. Lord ,  Christopher M. Dye

    IPC分类号： F02K3/02

    CPC分类号： F02C3/145 ,  F02C7/36 ,  F02K3/025 ,  F05D2250/314

    摘要： A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.

    摘要翻译： 燃气涡轮发动机包括安装成围绕第一轴线旋转的推进单元和安装成围绕第二轴线旋转的核心发动机，并且其中第一和第二轴线是不平行的。 燃气涡轮发动机包括由与推进单元相邻的自由涡轮机驱动的推进单元和相关联的风扇，并且具有包括压缩机，燃烧器和涡轮机部分的气体发生器核心发动机。 还公开了一种方法。

    Gas turbine engine compressor arrangement
    49.
    发明授权
    Gas turbine engine compressor arrangement 有权
    燃气涡轮发动机压缩机布置

    公开(公告)号：US08448895B2

    公开(公告)日：2013-05-28

    申请号：US13484361

    申请日：2012-05-31

    申请人： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

    发明人： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

    IPC分类号： B64D29/00

    CPC分类号： B64D27/26 ,  B64D2027/264 ,  B64D2027/266

    摘要： A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.

    摘要翻译： 燃气涡轮发动机包括风扇部分和包括低压压缩机部分的低阀芯。 低压压缩机部分包括八（8）个或更少的阶段。 高阀芯包括高压压缩机部分，其具有8至15（8-15）级。 整体压缩机压力比由低压压缩机部分和高压压缩机的组合提供。 齿轮系沿发动机中心线定义。 低阀芯可操作以通过齿轮系驱动风扇部分。

    SPOKED SPACER FOR A GAS TURBINE ENGINE
    50.
    发明申请
    SPOKED SPACER FOR A GAS TURBINE ENGINE 有权
    用于气体涡轮发动机的间隔器

    公开(公告)号：US20130108468A1

    公开(公告)日：2013-05-02

    申请号：US13283733

    申请日：2011-10-28

    申请人： Gabriel L. Suciu ,  Stephen P. Muron ,  Christopher M. Dye

    发明人： Gabriel L. Suciu ,  Stephen P. Muron ,  Christopher M. Dye

    IPC分类号： F01D5/08

    CPC分类号： F01D11/005 ,  F01D5/066 ,  F05D2240/55

    摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation and a plurality of core gas path seals which extend from the rotor ring, each of the plurality of core gas path seals extend from the rotor ring at an interface, the interface defined along a spoke.

    摘要翻译： 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环和从转子环延伸的多个芯气体通道密封件，多个芯气体通道密封件中的每一个在转子环的界面处延伸， 沿着辐条定义的界面。