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公开(公告)号：US20130108413A1
公开(公告)日：2013-05-02
申请号：US13459474
申请日：2012-04-30
申请人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , loannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , loannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
IPC分类号： F01D5/08
CPC分类号： F01D11/006 , F01D5/066
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘和与多个叶片相邻的至少一个间隔件延伸的多个叶片。 流动通道限定在转子盘和叶片和间隔件之间。 在间隔件内形成多个入口以将空气泵送到流动通道中。
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公开(公告)号：US08961132B2
公开(公告)日：2015-02-24
申请号：US13459474
申请日：2012-04-30
申请人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , Ioannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , Ioannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
CPC分类号： F01D11/006 , F01D5/066
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘和与多个叶片相邻的至少一个间隔件延伸的多个叶片。 流动通道限定在转子盘和叶片和间隔件之间。 在间隔件内形成多个入口以将空气泵送到流动通道中。
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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：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：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：US08468795B2
公开(公告)日：2013-06-25
申请号：US11718525
申请日：2004-12-01
IPC分类号： F02K3/02
摘要： A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages (144) at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage (80) toward an axial airflow direction through airflow aspiration at the potentially turbulent locations.
摘要翻译： 风扇 - 涡轮转子组件包括扩散器部分（114），其将来自径向芯气流通道（80）的气流朝向轴向气流方向扩散。 扩散器流动通道在一个位置处与扩散通道（144）连通，当气流从径向核心气流通道（80）通过在潜在湍流位置处的气流抽吸朝向轴向气流方向转动时，气流的分离减小。
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8.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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