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公开(公告)号：US07950220B2
公开(公告)日：2011-05-31
申请号：US11455980
申请日：2006-06-19
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。
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公开(公告)号：US20090317229A1
公开(公告)日：2009-12-24
申请号：US12138370
申请日：2008-06-12
IPC分类号： F02C9/18
CPC分类号： F01D17/162 , F02C9/20 , F04D27/0215 , F04D29/563 , Y02T50/671
摘要： An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.
摘要翻译： 用于燃气涡轮发动机的致动器模块包括安装在公共致动器壳体内的多个致动器。
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公开(公告)号：US20090236469A1
公开(公告)日：2009-09-24
申请号：US12052769
申请日：2008-03-21
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine.
摘要翻译： 用于燃气涡轮发动机的安装系统包括安装连杆组件和大致横向于安装连杆组件定位的切向连杆。 安装联动装置至少起反推力。 切向连杆至少响应燃气涡轮发动机的垂直载荷，侧向载荷和扭矩载荷。
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公开(公告)号：US20090191045A1
公开(公告)日：2009-07-30
申请号：US12019919
申请日：2008-01-25
IPC分类号： F01D1/26
CPC分类号： F01D5/026 , F01D5/03 , F02C7/36 , F05D2260/40311
摘要： A low pressure turbine for a gas turbine engine includes inner and outer counter-rotating rotor sets, with both said rotor sets driving a common shaft.
摘要翻译： 用于燃气涡轮发动机的低压涡轮机包括内部和外部反向旋转的转子组，所述转子组都驱动公共轴。
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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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公开(公告)号：US20080050220A1
公开(公告)日：2008-02-28
申请号：US11509241
申请日：2006-08-24
IPC分类号： F04D29/56
CPC分类号： F01D17/162 , F04D29/563 , F05D2250/314 , F05D2260/50 , F05D2260/79
摘要： A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.
摘要翻译： 一种可变的几何入口导向叶片组件，其减少放置在燃气涡轮发动机中的下游压缩机叶片上的应力。 本发明圆周倾斜上游导叶，径向推动发动机核心气流。 这样可以减少下游叶片上的空气动力学应力。 本发明通过提供一个铰链和一个联接在一致环上的球面轴承相结合来克服了协调环和叶片臂之间的运动差异。
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公开(公告)号：US10145266B2
公开(公告)日：2018-12-04
申请号：US13362237
申请日：2012-01-31
申请人： Brian D. Merry , Gabriel L. Suciu
发明人： Brian D. Merry , Gabriel L. Suciu
IPC分类号： F01D25/16
摘要： A gas turbine engine includes a shaft supported by first and second bearings for rotation relative to an inlet case. The first and second bearings are positioned within a common bearing compartment.
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公开(公告)号：US09957918B2
公开(公告)日：2018-05-01
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.
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