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公开(公告)号：US20090188334A1
公开(公告)日：2009-07-30
申请号：US12019742
申请日：2008-01-25
IPC分类号： F16H37/00
CPC分类号： F02C7/36 , F02C7/32 , F05D2220/76 , F05D2260/4031
摘要： Accessory gearboxes and related gas turbine engine systems are provided. In this regard, a representative accessory gearbox for a gas turbine engine is operative to be driven by rotational energy extracted from the gas turbine engine and imparted to the gearbox by multiple tower shafts.
摘要翻译： 提供附件齿轮箱和相关燃气涡轮发动机系统。 在这方面，用于燃气涡轮发动机的代表性附件齿轮箱可操作地由从燃气涡轮发动机提取的旋转能量驱动并通过多个塔轴传递给齿轮箱。
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公开(公告)号：US20090081035A1
公开(公告)日：2009-03-26
申请号：US11858988
申请日：2007-09-21
IPC分类号： F01D25/24
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：US20090056306A1
公开(公告)日：2009-03-05
申请号：US11846095
申请日：2007-08-28
摘要： A turbine engine is disclosed that includes a fan case surrounding a fan. A core is supported relative to the fan case by support structure, such as flow exit guide vanes, which are arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage. In one example, the example turbine engine includes a gear train arranged between the fan and a spool. The gear train is axially aligned and supported by the inlet case. An intermediate case is arranged axially adjacent to the compressor case. The support structure is arranged axially forward of the intermediate case. In one example, the support structure is axially aligned with the compressor case.
摘要翻译： 公开了一种涡轮发动机，其包括围绕风扇的风扇壳体。 通过诸如流出口导向叶片的支撑结构相对于风扇壳体支撑芯体，其布置在风扇的下游。 芯部包括具有入口壳体的芯壳体，其布置成接收来自风扇的气流。 压缩机壳体布置成与入口壳体相邻并围绕压缩机台。 在一个示例中，示例性涡轮发动机包括布置在风扇和阀芯之间的齿轮系。 齿轮系轴向对齐并由入口箱支撑。 中间壳体被布置成与压缩机壳体轴向相邻。 支撑结构被布置在中间壳体的轴向前方。 在一个示例中，支撑结构与压缩机壳体轴向对准。
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94.发明申请COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 有权带齿轮系统的逆转低压涡轮机安装在涡轮机排气箱公开(公告)号：US20130223993A1
公开(公告)日：2013-08-29
申请号：US13408301
申请日：2012-02-29
申请人： Brian D. Merry , Gabriel L. Suciu
发明人： Brian D. Merry , Gabriel L. Suciu
CPC分类号： F01D15/12 , F01D1/24 , F01D25/162 , F01D25/30 , F02C3/107 , F02C7/32 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
摘要翻译： 燃气涡轮发动机包括限定旋转轴线的轴。 外转子直接驱动轴并且包括一组外部叶片。 内转子具有与外组叶片交替散布的内组叶片。 内转子构造成围绕与外转子的旋转轴线相反的方向旋转。 齿轮系统将内转子连接到轴，并且构造成以比外部组叶片更快的速度旋转内组叶片。
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公开(公告)号：US20130223991A1
公开(公告)日：2013-08-29
申请号：US13407836
申请日：2012-02-29
IPC分类号： F01D15/12
CPC分类号： F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
摘要： A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
摘要翻译： 燃气涡轮发动机包括具有压缩机部分的核心发动机，燃烧器和涡轮机。 涡轮驱动输出轴，输出轴驱动至少四个齿轮。 所述至少四个齿轮中的每一个延伸穿过驱动轴以驱动相关联的风扇转子。
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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。
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97.发明申请公开(公告)号：US20120297791A1
公开(公告)日：2012-11-29
申请号：US13116116
申请日：2011-05-26
CPC分类号： F02C7/20 , F01D9/041 , F01D25/30 , F02K1/04 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/4932
摘要： A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
摘要翻译： 用于燃气涡轮发动机的涡轮机排气箱包括在CMC核心机舱后部和CMC尾锥之间的多个CMC涡轮机排气外壳支柱。
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98.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：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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