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公开(公告)号：US08267349B2
公开(公告)日：2012-09-18
申请号：US13336140
申请日：2011-12-23
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine.
摘要翻译： 根据本发明的示例性方面的燃气涡轮发动机包括沿发动机中心线轴线限定的齿轮系和沿着发动机中心线轴线驱动齿轮系的线轴，所述线轴包括低阶数低压涡轮机。
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公开(公告)号：US20120159966A1
公开(公告)日：2012-06-28
申请号：US13414118
申请日：2012-03-07
CPC分类号： F02C7/32 , F01D25/18 , F05D2260/403 , Y10T29/49464
摘要： An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct.
摘要翻译： 用于燃气涡轮发动机的组件包括中间壳体和变速箱。 中间壳体限定环形过渡管道。 齿轮箱包括多个叶片，并与环形过渡管道整体形成。
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23.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
IPC分类号： F02C9/00
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。
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公开(公告)号：US08104289B2
公开(公告)日：2012-01-31
申请号：US11868982
申请日：2007-10-09
IPC分类号： F02C7/00
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.
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公开(公告)号：US08075261B2
公开(公告)日：2011-12-13
申请号：US11858988
申请日：2007-09-21
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。
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公开(公告)号：US20110127368A1
公开(公告)日：2011-06-02
申请号：US12629317
申请日：2009-12-02
IPC分类号： B64D27/10
CPC分类号： B64D27/20 , B64D27/26 , B64D2027/268 , Y02T50/44
摘要： A mounting system for a gas turbine engine assembly includes a plurality of mounting links attached the gas turbine engine along a single plane transverse to the engine centerline for separating the loads from the core engine.
摘要翻译： 用于燃气涡轮发动机组件的安装系统包括沿着与发动机中心线横向的单个平面连接燃气涡轮发动机的多个安装链路，用于将负载与核心发动机分离。
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公开(公告)号：US20090188234A1
公开(公告)日：2009-07-30
申请号：US12019837
申请日：2008-01-25
CPC分类号： F02K3/115 , F02C7/14 , F02C7/185 , F02C7/224 , Y02T50/671 , Y02T50/675
摘要： A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.
摘要翻译： 热管理系统包括以至少部分系列关系布置的多个热交换器中的至少两个。
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公开(公告)号：US20090188232A1
公开(公告)日：2009-07-30
申请号：US12020728
申请日：2008-01-28
CPC分类号： F02K3/06 , B64D27/18 , B64D29/00 , B64D33/10 , F02C6/08 , F02C7/14 , F02C7/185 , F02C7/224 , F02K3/115 , Y02T50/44 , Y02T50/671 , Y02T50/675
摘要： A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placement schemes.
摘要翻译： 热管理系统包括与燃气涡轮发动机的旁路流相通的至少一个热交换器。 热交换器的放置使重量和空气动力学损失最小化，并且有助于整体性能提高超过传统的管道式热交换器放置方案。
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公开(公告)号：US20090180864A1
公开(公告)日：2009-07-16
申请号：US12013617
申请日：2008-01-14
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。
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公开(公告)号：US20200284222A1
公开(公告)日：2020-09-10
申请号：US16405149
申请日：2019-05-07
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： F02K3/06 , F02C9/20 , F02C9/18 , B64D27/26 , F02C7/36 , F02C3/107 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C7/20 , F02K1/15
摘要： A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
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