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公开(公告)号：US08365511B2
公开(公告)日：2013-02-05
申请号：US11720543
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Brian Merry
IPC分类号： F02K3/02
摘要： A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inwardly from the rear case. The exhaust mixer extends in a flow path of a combustor to mix a high energy gas stream from the combustor with bypass air from a bypass fan. The engine mounts are located on the periphery of the rear case for mounting the engine to an aircraft. The rear case, exit guide vanes, exhaust mixer, and engine mounts form a unitary engine support structure which is installable as a single piece into an engine.
摘要翻译： 尖端涡轮发动机组件包括具有后壳体，出口导向叶片，排气混合器和发动机支架的发动机支撑结构。 后壳围绕发动机中心线设置。 出口导向叶片从后壳径向向内延伸。 排气混合器在燃烧器的流路中延伸，以将来自燃烧器的高能气流与旁路风扇的旁路空气混合。 发动机支架位于后壳的外围，用于将发动机安装到飞机上。 后壳体，出口导向叶片，排气混合器和发动机支架形成一体的发动机支撑结构，其可作为单件安装到发动机中。
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公开(公告)号：US08152469B2
公开(公告)日：2012-04-10
申请号：US11719855
申请日：2004-12-01
摘要： A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.
摘要翻译： 风扇 - 涡轮转子组件（24）包括一个或多个涡轮环转子（32）。 每个涡轮机环形转子都被铸造为一个整体的环形环。 通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏最小化，这增加了发动机效率。 涡轮环转子到扩散器环（114）的组装包括每个涡轮环转子的轴向安装和径向锁定。
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3.发明授权Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine 有权具有整体扩散器部分和尖端涡轮机叶片部分的风扇叶片，用于尖端涡轮发动机公开(公告)号：US07887296B2
公开(公告)日：2011-02-15
申请号：US11719755
申请日：2004-12-01
CPC分类号： F01D5/3007 , F01D1/023 , F01D1/06 , F01D5/022 , F01D5/147 , F01D5/30 , Y02T50/672
摘要： A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.
摘要翻译： 用于尖端涡轮发动机的风扇涡轮机转子组件包括由许多细长开口扇形的外周，所述多个细长开口限定了用于容纳导流部分和中空风扇叶片部分的诱导器接收部分。 每个风扇叶片部分包括从扩散器部分延伸的涡轮部分。
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公开(公告)号：US09845727B2
公开(公告)日：2017-12-19
申请号：US11720463
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Brian Merry
CPC分类号： F02C3/073 , F02K1/04 , F02K3/068 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y10T29/49346
摘要： A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
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公开(公告)号：US09109537B2
公开(公告)日：2015-08-18
申请号：US11720470
申请日：2004-12-04
申请人： Gabriel L. Suciu , James W. Norris , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Brian Merry
摘要： A tip turbine engine assembly (8) includes a fan (32) rotatable in a fan plane (22) about an engine centerline (112). The fan (32) includes a fan blade (34) that defines a core airflow passage therethrough. An engine case (10) surrounds and supports the fan and engine. A plurality of engine mounts (20) for mounting the engine to an aircraft are positioned circumferentially about the outside of the engine case in a single mounting plane (22) that is perpendicular to the engine centerline.
摘要翻译： 顶端涡轮发动机组件（8）包括可围绕发动机中心线（112）在风扇平面（22）中旋转的风扇（32）。 风扇（32）包括限定通过其中的芯气流通道的风扇叶片（34）。 发动机壳体（10）围绕并支撑风扇和发动机。 用于将发动机安装到飞行器的多个发动机支架（20）在垂直于发动机中心线的单个安装平面（22）中周向地围绕发动机壳体的外部定位。
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公开(公告)号：US08672630B2
公开(公告)日：2014-03-18
申请号：US13350937
申请日：2012-01-16
摘要： A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor.
摘要翻译： 风扇 - 涡轮转子组件包括一个或多个涡轮机环形转子。 每个涡轮机环形转子都被铸造为一个整体的环形环。 通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏最小化，这增加了发动机效率。 涡轮环转子到扩散器环的组装包括每个涡轮环转子的轴向安装和径向锁定。
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7.发明授权Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method 有权可变风机入口导叶组件，具有这种组件的涡轮发动机及相应的控制方法公开(公告)号：US08276362B2
公开(公告)日：2012-10-02
申请号：US13022456
申请日：2011-02-07
IPC分类号： F02K3/02
CPC分类号： F01D17/162 , F02C3/073 , F02K3/068
摘要： A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
摘要翻译： 涡轮发动机包括多个可变风扇入口导向叶片。 在涡轮发动机是顶端涡轮发动机的情况下，即使风扇 - 涡轮转子组件以固定的速率直接联接到轴向压缩机，可变风扇入口导叶允许控制发动机稳定性的能力。 风扇入口导向叶片可以从风扇入口导叶的内径致动。
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公开(公告)号：US20120167593A1
公开(公告)日：2012-07-05
申请号：US13346213
申请日：2012-01-09
摘要： A gearbox support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing support the epicyclic gear arrangement.
摘要翻译： 用于涡轮发动机的齿轮箱支撑组件包括行星齿轮装置和第一锥形轴承以及与第一锥形轴承间隔开的第二锥形轴承。 第一锥形轴承和第二锥形轴承支撑行星齿轮装置。
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公开(公告)号：US08033092B2
公开(公告)日：2011-10-11
申请号：US11720539
申请日：2004-12-01
IPC分类号： F02K3/02
CPC分类号： F01D5/187 , F01D1/023 , F01D5/022 , F01D21/045 , F02C3/045 , F02C3/08 , F02C3/107 , F05D2300/433 , Y02T50/676
摘要： A tip turbine engine assembly includes an integral engine outer case located radially outward from a fan assembly. The integral outer case includes a rear portion and a forward portion with an arcuate portion that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment. Fan inlet guide vanes are integrally formed with the arcuate portion to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally formed in a casting process.
摘要翻译： 顶端涡轮发动机组件包括从风扇组件径向向外定位的一体式发动机外壳。 一体的外壳包括后部和具有弓形部分的向前部分，其径向向内弯曲以形成隔间。 环形燃烧器容纳并安装在隔室中。 风扇入口导向叶片与弓形部分一体地形成，以形成一体的壳体部分。 后部，前部和风扇入口导向叶片在铸造过程中一体地形成。
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公开(公告)号：US07927075B2
公开(公告)日：2011-04-19
申请号：US11719757
申请日：2004-12-01
CPC分类号： F01D5/02 , F01D5/022 , F01D5/3007 , F02C3/073 , F02K3/068 , F04D25/045 , F04D29/54 , F05D2240/55 , F05D2260/30 , F05D2300/603 , Y02T50/672 , Y10T29/49321
摘要： A fan-turbine rotor assembly (24) for a tip turbine engine (10 )includes a fan hub (64) with an outer periphery (112) scalloped by a multitude of elongated openings (114) which extend into a fan hub web (115). Each elongated opening defines an inducer receipt section (117) to receive an inducer section (66)and a hollow fan blade section (72). An inducer exhaust from each inducer section is located adjacent a core airflow passage (80) within each fan blade section to provide communication therebetween.
摘要翻译： 一种用于尖端涡轮发动机（10）的风扇涡轮机转子组件（24）包括风扇轮毂（64），其具有由多个细长的开口（114）扇形的外周边（112），所述多个细长的开口延伸到风扇轮毂腹板 ）。 每个细长的开口限定了一个诱导器收容部分（117），用于容纳一个导流部分（66）和一个中空的风扇叶片部分（72）。 来自每个引导部分的诱导物排放物位于每个风扇叶片部分内的核心气流通道80附近，以在它们之间提供连通。
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