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    Gas turbine engine compressor arrangement
    104.
    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：US08277174B2

    公开(公告)日：2012-10-02

    申请号：US13418457

    申请日：2012-03-13

    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： 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 low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

    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。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而高压压缩机部分的压力比为约7至约15。

    SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES
    105.
    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
    108.
    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
    110.
    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。