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公开(公告)号：US08448895B2
公开(公告)日：2013-05-28
申请号：US13484361
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
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
摘要翻译： 燃气涡轮发动机包括风扇部分和包括低压压缩机部分的低阀芯。 低压压缩机部分包括八（8）个或更少的阶段。 高阀芯包括高压压缩机部分，其具有8至15（8-15）级。 整体压缩机压力比由低压压缩机部分和高压压缩机的组合提供。 齿轮系沿发动机中心线定义。 低阀芯可操作以通过齿轮系驱动风扇部分。
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公开(公告)号：US20130108466A1
公开(公告)日：2013-05-02
申请号：US13283710
申请日：2011-10-28
CPC分类号： F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
摘要翻译： 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。
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公开(公告)号：US20130108445A1
公开(公告)日：2013-05-02
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.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片，所述多个叶片中的每一个叶片在接合处从转子盘延伸，所述界面沿辐条限定。
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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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15.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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公开(公告)号：US20120234017A1
公开(公告)日：2012-09-20
申请号：US13483426
申请日：2012-05-30
摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.
摘要翻译： 燃气涡轮发动机包括低压压缩机部分和高压压缩机部分。 低压涡轮机驱动低压压缩机部分。 齿轮装置由低压涡轮机驱动，从而驱动风扇部分。 低压压缩机部分的压力比在大约4-8之间，并且高压压缩机部分的压力比在大约8-15之间。 在单独的特征中，压缩机壳体包括前压缩机壳体部分和后压缩机壳体部分，后压缩机壳体部分比从前压缩机壳体部分的入口壳体更远离轴向。 支撑构件在风扇部分和前压缩机壳体部分之间延伸。
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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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19.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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