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324 条记录 (耗时 0.03 秒)

    GEARED TURBOFAN BEARING ARRANGEMENT
    134.
    发明申请
    GEARED TURBOFAN BEARING ARRANGEMENT 有权
    齿轮式涡轮轴承安装

    公开(公告)号：US20130025258A1

    公开(公告)日：2013-01-31

    申请号：US13193790

    申请日：2011-07-29

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

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

    IPC分类号： F02K3/02

    CPC分类号： F02C7/06 ,  F01D25/16 ,  F05D2240/50

    摘要： A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.

    摘要翻译： 齿轮涡轮风扇燃气涡轮发动机包括风扇部分和芯部分。 核心部分包括压缩机部分，燃烧器部分和涡轮部分。 风扇部分包括齿轮箱和风扇。 低阀芯包括在涡轮机部分内的低涡轮机和与用于驱动风扇的齿轮箱的前向连接。 支撑支架用于通过前滚子轴承在最向前的位置绕轴线旋转，并在后部位置由推力轴承旋转。

    SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES
    136.
    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：US20120216548A1

    公开(公告)日：2012-08-30

    申请号：US13466745

    申请日：2012-05-08

    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： F02C7/00

    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 method for reducing overspeed potential of a turbine of a gas turbine engine includes: providing a first load to the turbine via a first torque path; providing a second load to the turbine via a second torque path; and operating the turbine such that: mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path; and mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path.

    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，用于降低燃气涡轮发动机的涡轮机的超速电位的代表性方法包括：经由第一扭矩路径向涡轮机提供第一负载; 经由第二扭矩路径向所述涡轮机提供第二负载; 并且操作所述涡轮机，使得限定所述第一扭矩路径的至少一部分的部件的机械故障不阻止所述第二负载经由所述第二扭矩路径施加到所述涡轮机; 并且限定第二扭矩路径的部件的机械故障不阻止第一负载经由第一扭矩路径施加到涡轮机。

    Gas turbine engine case
    138.
    发明授权
    Gas turbine engine case 有权
    燃气涡轮发动机外壳

    公开(公告)号：US08162605B2

    公开(公告)日：2012-04-24

    申请号：US12013617

    申请日：2008-01-14

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

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

    IPC分类号： F01D25/28

    CPC分类号： F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F05D2230/60 ,  Y02T50/671 ,  Y10T29/49826

    摘要： A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.

    摘要翻译： 燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。 在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。

    Gas turbine engine front architecture modularity
    139.
    发明授权
    Gas turbine engine front architecture modularity 有权
    燃气轮机发动机前架构模块化

    公开(公告)号：US07955046B2

    公开(公告)日：2011-06-07

    申请号：US11860719

    申请日：2007-09-25

    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： F01D25/24

    CPC分类号： F02C7/36 ,  F02C7/04 ,  F02K3/06 ,  F05D2230/60

    摘要： A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.

    摘要翻译： 公开了一种燃气涡轮发动机，其包括具有压缩机部分的阀芯。 入口壳体在压缩机部分的轴向上游设置。 齿轮箱固定在入口箱上。 齿轮箱连接线轴和风扇。 密封组件布置在入口壳体和齿轮箱之间以提供密封的轴承隔室。 入口箱，齿轮箱和密封组件提供一个模块。 紧固元件将模块可拆卸地固定到线轴上。 燃气涡轮发动机可以通过将紧固元件与发动机芯断开来进行维修。 齿轮箱和进气口箱可以作为模块从发动机内芯上拆下，而不必拆卸变速箱。

    Turbine engine compressor
    140.
    发明授权
    Turbine engine compressor 有权
    涡轮发动机压缩机

    公开(公告)号：US07950220B2

    公开(公告)日：2011-05-31

    申请号：US11455980

    申请日：2006-06-19

    申请人： Brian D. Merry ,  Gabriel L. Suciu ,  John P. Nikkanen

    发明人： Brian D. Merry ,  Gabriel L. Suciu ,  John P. Nikkanen

    IPC分类号： F02K3/00

    CPC分类号： F02K3/072 ,  F02C3/067 ,  F02C3/107 ,  F05D2260/40 ,  F05D2260/40311

    摘要： A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least two compressor blade stage and at least two turbine blade stage. A combustor is located between the at least two compressor blade stage and the at least two turbine blade stage along a core flowpath. The at least two counter-rotating compressor blade stage is interspersed with the first spool at least two compressor blade stage. A transmission couples the at least two additional compressor blade stage to the first spool for counter-rotation about the engine axis.

    摘要翻译： 代替定子级的反向旋转叶片级可以补偿燃气涡轮发动机滑阀的相对较低的转速。 第一阀芯可以具有至少两个压缩机叶片级和至少两个涡轮叶片级。 燃烧器沿核心流路位于至少两个压缩机叶片级和至少两个涡轮叶片级之间。 所述至少两个反向旋转的压缩机叶片级与所述第一卷轴分布至少两个压缩机叶片级。 传动装置将至少两个额外的压缩机叶片级联接到第一卷轴以围绕发动机轴线反转。