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公开(公告)号：US20130014489A1
公开(公告)日：2013-01-17
申请号：US13484400
申请日：2012-05-31
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
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
摘要翻译： 燃气涡轮发动机包括沿发动机中心线轴线驱动齿轮系的线轴。
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公开(公告)号：US20120315130A1
公开(公告)日：2012-12-13
申请号：US13590399
申请日：2012-08-21
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 high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45.
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。 通过所述低压压缩机部分上的压力比和所述高压压缩机部分之间的压力比的组合提供的总压力比大于约35.跨过高压压缩机部分的压力比介于约 7和15左右，风扇部分的压力比小于或等于1.45。
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13.发明申请公开(公告)号：US20120301312A1
公开(公告)日：2012-11-29
申请号：US13116093
申请日：2011-05-26
CPC分类号： F01D5/282 , C04B37/00 , C04B2235/5244 , C04B2237/365 , C04B2237/38 , C04B2237/76 , F01D5/147 , F01D5/284 , F01D9/041 , F01D25/246 , F05D2240/12 , F05D2300/6033 , Y10T29/49321
摘要： A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine includes a box-shape fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line.
摘要翻译： 用于燃气涡轮发动机的陶瓷基体复合材料（CMC）翼型段包括限定直线压力侧粘合线和直线吸力侧粘合线的箱形纤维几何形状。
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14.发明申请INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR DISK HUB GEOMETRY FOR A GAS TURBINE ENGINE 有权集成陶瓷基复合材料转子盘式汽油发动机几何公开(公告)号：US20120301305A1
公开(公告)日：2012-11-29
申请号：US13116076
申请日：2011-05-26
IPC分类号： F01D5/30
摘要： A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.
摘要翻译： 用于燃气涡轮发动机的转子盘包括CMC轮毂和与CMC轮毂相对的多个CMC翼型件集成的轨道，轨道限定了轨道平台部分，该轨道平台部分向轨道内孔逐渐变细。
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公开(公告)号：US20120288366A1
公开(公告)日：2012-11-15
申请号：US13294492
申请日：2011-11-11
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：US08256707B2
公开(公告)日：2012-09-04
申请号：US11832107
申请日：2007-08-01
IPC分类号： B64D27/00
CPC分类号： F02C7/20 , B64D27/18 , B64D27/26 , B64D2027/268 , Y02T50/44 , Y10T29/49826
摘要： An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.
摘要翻译： 发动机安装配置可使发动机推力在后方安装。 发动机安装配置减少了发动机的主干弯曲，中间壳失真和内部机舱内的释放空间。
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公开(公告)号：US20120167592A1
公开(公告)日：2012-07-05
申请号：US13414763
申请日：2012-03-08
IPC分类号： F02C7/20
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：US20090290976A1
公开(公告)日：2009-11-26
申请号：US12154200
申请日：2008-05-21
IPC分类号： F01D15/12
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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公开(公告)号：US09938831B2
公开(公告)日：2018-04-10
申请号：US13283689
申请日：2011-10-28
申请人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
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公开(公告)号：US09816441B2
公开(公告)日：2017-11-14
申请号：US12413634
申请日：2009-03-30
IPC分类号： F02C7/32
CPC分类号： F02C7/32 , Y02T50/671
摘要： An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis.
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