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324 条记录 (耗时 0.034 秒)

    THREE SPOOL ENGINE BEARING CONFIGURATION
    34.
    发明申请
    THREE SPOOL ENGINE BEARING CONFIGURATION 有权
    三座发动机轴承配置

    公开(公告)号：US20130025257A1

    公开(公告)日：2013-01-31

    申请号：US13193757

    申请日：2011-07-29

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

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

    IPC分类号： F02K3/02

    CPC分类号： F02C7/06 ,  F01D25/162 ,  F02C3/107 ,  F05D2260/40311

    摘要： A disclosed gas turbine engine includes a core section having a low spool, intermediate spool and a high spool that rotate about a common axis. The intermediate spool is supported at an aft position by an inter-shaft bearing arrangement on the low spool. The low spool is supported for rotation in an aft position by an aft roller bearing supported on a turbine exhaust case of the gas turbine engine. The high spool is supported by a high spool aft roller bearing disposed within a high spool bearing compartment. The high spool bearing compartment is positioned within a radial space between the combustor and the axis.

    摘要翻译： 所公开的燃气涡轮发动机包括具有低卷轴，中间卷轴和围绕公共轴线旋转的高卷轴的芯部分。 中间阀芯通过位于低阀芯上的轴间轴承装置在后方支撑。 通过支撑在燃气涡轮发动机的涡轮机排气箱上的后滚子轴承，支撑着低滑阀在后方转动。 高卷轴由设置在高卷轴轴承隔室内的高卷轴后滚轮轴承支撑。 高卷筒轴承室位于燃烧器和轴线之间的径向空间内。

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    36.
    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：US20120234017A1

    公开(公告)日：2012-09-20

    申请号：US13483426

    申请日：2012-05-30

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

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

    IPC分类号： F02C3/10 ,  F02C7/36 ,  F02C7/20

    CPC分类号： F02C3/107 ,  F02K3/06

    摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.

    摘要翻译： 燃气涡轮发动机包括低压压缩机部分和高压压缩机部分。 低压涡轮机驱动低压压缩机部分。 齿轮装置由低压涡轮机驱动，从而驱动风扇部分。 低压压缩机部分的压力比在大约4-8之间，并且高压压缩机部分的压力比在大约8-15之间。 在单独的特征中，压缩机壳体包括前压缩机壳体部分和后压缩机壳体部分，后压缩机壳体部分比从前压缩机壳体部分的入口壳体更远离轴向。 支撑构件在风扇部分和前压缩机壳体部分之间延伸。

    SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES
    39.
    发明申请
    SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES 有权
    涉及气体涡轮发动机的多个扭矩模块的系统和方法

    公开(公告)号：US20120090329A1

    公开(公告)日：2012-04-19

    申请号：US13336807

    申请日：2011-12-23

    申请人： Michael E. McCune ,  Brian D. Merry ,  Gabriel L. Suciu

    发明人： Michael E. McCune ,  Brian D. Merry ,  Gabriel L. Suciu

    IPC分类号： F02C9/00

    CPC分类号： F01D21/02 ,  F01D21/04 ,  F01D25/16 ,  F02C3/107 ,  F02C7/36 ,  F05D2270/091

    摘要： Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other.

    摘要翻译： 提供了涉及燃气涡轮发动机的多个扭矩路径的系统和方法。 在这方面，包括压缩机，涡轮机和齿轮组件的用于燃气涡轮发动机的代表性阀芯组件包括：可操作地由涡轮机驱动的轴; 用于将轴连接到压缩机的第一卷轴段; 以及用于将所述轴联接到所述齿轮组件的第二线轴段。 第一卷轴段和第二卷轴段不彼此连接。