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    GEARED TURBOMACHINE ARCHITECTURE HAVING A LOW PROFILE CORE FLOW PATH CONTOUR
    52.
    发明申请
    GEARED TURBOMACHINE ARCHITECTURE HAVING A LOW PROFILE CORE FLOW PATH CONTOUR 审中-公开
    具有低剖面圆锥滚子路径的齿轮式涡轮机结构

    公开(公告)号：US20130195645A1

    公开(公告)日：2013-08-01

    申请号：US13364798

    申请日：2012-02-02

    申请人： Gabriel L. Suciu ,  Brian D. Merry ,  Karl L. Hasel

    发明人： Gabriel L. Suciu ,  Brian D. Merry ,  Karl L. Hasel

    IPC分类号： F04D19/00

    CPC分类号： F02K3/06 ,  F02C3/107 ,  F02C7/04 ,  F04D29/522 ,  F05D2260/40311 ,  F05D2270/17

    摘要： An exemplary geared turbomachine assembly includes a core inlet having a radially inner boundary that is spaced a first radial distance from a rotational axis of a turbomachine, and a compressor section inlet having a radially inner boundary that is spaced a second radial distance from the rotational axis. A ratio of the second radial distance to the first radial distance is of about 0.65 to about 0.9.

    摘要翻译： 示例性的齿轮涡轮机组件包括具有径向内边界的芯入口，该径向内边界与涡轮机的旋转轴线间隔开第一径向距离，以及压缩机部分入口，其具有径向内边界，该径向内边界与旋转轴线间隔开第二径向距离 。 第二径向距离与第一径向距离的比率为约0.65至约0.9。

    ACCESSORY GEARBOX BUFFER COOLING AIR PUMP SYSTEM
    54.
    发明申请
    ACCESSORY GEARBOX BUFFER COOLING AIR PUMP SYSTEM 有权
    附件齿轮缓冲器冷却空气泵系统

    公开(公告)号：US20130047623A1

    公开(公告)日：2013-02-28

    申请号：US13219913

    申请日：2011-08-29

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

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

    IPC分类号： F02C3/10 ,  F02C6/00

    CPC分类号： F02K3/00 ,  F01D25/125 ,  F02C7/32 ,  F05D2260/4031

    摘要： A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.

    摘要翻译： 缓冲空气泵为燃气涡轮发动机的冷却部件提供加压冷却空气。 缓冲空气泵支撑在附件齿轮箱上和/或内部，并通过入口歧管抽吸旁路空气。 支撑在涡旋壳体内的叶轮对进入的旁路空气加压并将加压空气通过通道引导到需要冷却的部件。 缓冲空气泵从旁路流入相对较冷的空气，用叶轮对空气加压，并将空气通过燃气涡轮发动机内的管道和通道送到需要冷却的部件，例如轴承组件。

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    56.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 有权
    燃气涡轮发动机压缩机装置

    公开(公告)号：US20120315130A1

    公开(公告)日：2012-12-13

    申请号：US13590399

    申请日：2012-08-21

    申请人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    发明人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC分类号： F01D1/06 ,  F01D15/12 ,  F01D25/28

    CPC分类号： F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

    摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45.

    摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过所述低压压缩机部分上的压力比和所述高压压缩机部分之间的压力比的组合提供的总压力比大于约35.跨过高压压缩机部分的压力比介于约 7和15左右，风扇部分的压力比小于或等于1.45。

    GAS TURBINE ENGINE COMPRESSOR CASE MOUNTING ARRANGEMENT
    59.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR CASE MOUNTING ARRANGEMENT 有权
    气体涡轮发动机压缩机壳体安装布置

    公开(公告)号：US20120288366A1

    公开(公告)日：2012-11-15

    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： F01D25/28

    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。