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公开(公告)号：US20080019830A1
公开(公告)日：2008-01-24
申请号：US11720470
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Brian Merry
发明人： Gabriel Suciu , James Norris , Brian Merry
IPC分类号： F01D25/28
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：US20080092514A1
公开(公告)日：2008-04-24
申请号：US11720463
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Brian Merry
发明人： Gabriel Suciu , James Norris , Brian Merry
IPC分类号： F02K1/04
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.
摘要翻译： 尖端涡轮发动机中的非金属尾管（202）包括围绕中心轴线设置（208）的锥形壁结构。 非金属尾管紧固在顶端涡轮发动机的后部的结构框架（44）上。 尖端涡轮发动机产生来自第一输出源的第一温度气体流和来自第二输出源的第二温度气体流。 第二温度气体流是比第一温度气体流更低的温度。 第二温度气流在末端涡轮发动机的内径处在尾骨的外表面上排出。 在内径处排出较冷的第二温度气流允许非金属物质用于形成尾骨。
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公开(公告)号：US20080008583A1
公开(公告)日：2008-01-10
申请号：US11720543
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Brian Merry
发明人： Gabriel Suciu , James Norris , Brian Merry
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：US20110200424A1
公开(公告)日：2011-08-18
申请号：US13089450
申请日：2011-04-19
申请人： Gabriel Suciu , Brian Merry , Michael E. McCune
发明人： Gabriel Suciu , Brian Merry , Michael E. McCune
IPC分类号： F01D1/26
CPC分类号： F02C3/08 , F02C3/073 , F02C3/107 , F02C7/36 , F02K3/068 , F04D25/045 , F05D2260/40311 , F16H48/10
摘要： A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.
摘要翻译： 尖端涡轮发动机提供相对于风扇反向旋转的轴向压缩机转子。 行星齿轮组将风扇的旋转耦合到轴向压缩机转子，使得轴向压缩机转子通过风扇沿与风扇相反的旋转方向的旋转来驱动。 通过逆向旋转轴向压缩机转子，消除了在压缩机叶片的最后阶段和到风扇的中空风扇叶片的入口之间的压缩机叶片的最后阶段。 结果，轴流压缩机的长度和末端涡轮发动机的总长度减小。
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公开(公告)号：US07937927B2
公开(公告)日：2011-05-10
申请号：US11719224
申请日：2004-12-01
申请人： Gabriel Suciu , Brian Merry , Michael E. McCune
发明人： Gabriel Suciu , Brian Merry , Michael E. McCune
IPC分类号： F02C1/06
CPC分类号： F02C3/08 , F02C3/073 , F02C3/107 , F02C7/36 , F02K3/068 , F04D25/045 , F05D2260/40311 , F16H48/10
摘要： A tip turbine engine (10) provides an axial compressor rotor (46) that is counter-rotated relative to a fan (24). A planetary gearset (90) couples rotation of a fan (46) to an axial compressor rotor (46), such that the axial compressor rotor (46) is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes (54) between the final stage of compressor blades (52) and inlets (66) to the hollow fan blades (28) of the fan are eliminated. As a result, the length of the axial compressor (22) and the overall length of the tip turbine engine (10) are decreased.
摘要翻译： 顶端涡轮发动机（10）提供相对于风扇（24）反向旋转的轴向压缩机转子（46）。 行星齿轮组（90）将风扇（46）的旋转与轴向压缩机转子（46）联接，使得轴向压缩机转子（46）通过风扇旋转方向与风扇相反的方向驱动。 通过反向旋转轴向压缩机转子，消除了在压缩机叶片（52）的最后级和到风扇的中空风扇叶片（28）的入口（66）之间的压缩机叶片（54）的最后级。 结果，轴流式压缩机22的长度和末端涡轮发动机10的总长度减小。
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公开(公告)号：US20090232650A1
公开(公告)日：2009-09-17
申请号：US11719887
申请日：2004-12-01
申请人： Gabriel Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
发明人： Gabriel Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
IPC分类号： F01D9/00
摘要： A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.
摘要翻译： 尖端涡轮发动机具有从中空风扇叶片通过燃烧器和燃烧器的燃烧室的更有效的核心气流路径。 涡轮发动机包括具有多个径向延伸的风扇叶片的可旋转风扇，每个风扇叶片限定其径向延伸的压缩机室。 涡轮机安装在风扇的外周。 在每个压缩机室的径向外端处的扩散器使得通过压缩机室的核心气流朝向燃烧器。 来自中空风扇叶片中的压缩机室的高速，高压核心气流在压缩空气流进入燃烧器之前扩散，从而提高顶端涡轮发动机的效率。 此外，通过在不直接径向向外的风扇叶片的外部的扩散器壳体的布置来减小顶端涡轮发动机的总直径。
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公开(公告)号：US07249929B2
公开(公告)日：2007-07-31
申请号：US10713641
申请日：2003-11-13
IPC分类号： F01D25/14
CPC分类号： F04D19/02 , F01D17/105 , F01D25/162 , F04D27/0215 , F04D27/023 , F04D29/545 , Y10T29/49323
摘要： A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and has a number of valve ports. At least a portion of the structural case extends structurally between the fore and aft joints. A valve element is shiftable between first and second conditions for respectively blocking and not blocking communication through the valve ports.
摘要翻译： 燃气涡轮发动机压缩机具有多个护罩环，至少其中一个排气口限定了多个排放口。 结构轮毂在护罩环的下游并相对于护罩环固定。 结构轮毂壳从与结构轮毂的后接头延伸到具有连接的一个护罩环的前接头并且具有多个阀口。 结构壳体的至少一部分在结构上在前后关节之间延伸。 阀元件可在第一和第二条件之间移动，以分别阻塞并阻止通过阀口的连通。
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公开(公告)号：US20080093174A1
公开(公告)日：2008-04-24
申请号：US11718429
申请日：2004-12-01
申请人： Gabriel Suciu , Brian Merry
发明人： Gabriel Suciu , Brian Merry
摘要： A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters the tailcone section through an annular tailcone exhaust nozzle entrance to transfer thermal energy into the combined airflow out of the engine to recover thrust loss ducted from the fan bypass stream.
摘要翻译： 液体 - 空气热交换器从发动机润滑流体系统中提取热能。 液体 - 空气热交换器位于尾部部分内，并且与通过环形尾气排气喷嘴入口进入尾部部分的风扇旁路气流的一部分连通，以将热能传递到从发动机外部的组合气流中以回收 从风扇旁路流引导的推力损失。
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公开(公告)号：US20050106009A1
公开(公告)日：2005-05-19
申请号：US10713641
申请日：2003-11-13
CPC分类号： F04D19/02 , F01D17/105 , F01D25/162 , F04D27/0215 , F04D27/023 , F04D29/545 , Y10T29/49323
摘要： A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and has a number of valve ports. At least a portion of the structural case extends structurally between the fore and aft joints. A valve element is shiftable between first and second conditions for respectively blocking and not blocking communication through the valve ports.
摘要翻译： 燃气涡轮发动机压缩机具有多个护罩环，至少其中一个排气口限定了多个排放口。 结构轮毂在护罩环的下游并相对于护罩环固定。 结构轮毂壳从与结构轮毂的后接头延伸到具有连接的一个护罩环的前接头并且具有多个阀口。 结构壳体的至少一部分在结构上在前后关节之间延伸。 阀元件可在第一和第二条件之间移动，以分别阻塞并阻止通过阀口的连通。
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公开(公告)号：US09003759B2
公开(公告)日：2015-04-14
申请号：US11719799
申请日：2004-12-01
申请人： Gabriel Suciu , Gary D. Roberge , Brian Merry
发明人： Gabriel Suciu , Gary D. Roberge , Brian Merry
摘要： A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than the maximum radius (25). The trailing surface (56) of the particle separator (20) is tapered and/or curved radially inwardly away from the maximum radius (25). Air flowing toward the core airflow inlet is first diverted radially outwardly by the inclined leading surface (24) of the particle separator (20) to the maximum radius (25) of the particle separator (20). The air then follows the trailing surface (56) radially inwardly to flow axially into the core airflow inlet. While the air can follow the contours of the particle separator (20) around the maximum radius (25) and into the core airflow inlet, any particles, such as dirt, will have more inertia and will pass radially outwardly of the core airflow inlet through the bypass fan.
摘要翻译： 用于尖端涡轮发动机（10）的颗粒分离器（20）包括通向圆锥形的倾斜前导表面（24），其导致最大半径（25）和锥形后表面（56），所述锥形后表面在所有点处具有小于 最大半径（25）。 颗粒分离器（20）的后表面（56）从最大半径（25）向内径向向内渐缩和/或弯曲。 首先通过颗粒分离器（20）的倾斜引导表面（24）向颗粒分离器（20）的最大半径（25）径向向外转向空气流向核心气流入口。 然后空气径向向内跟随后表面（56），从而轴向流入核心气流入口。 当空气可以沿着最大半径（25）和颗粒气流入口跟随颗粒分离器（20）的轮廓时，任何颗粒（例如污物）将具有更大的惯性并且将通过核心气流入口的径向向外通过 旁路风扇。
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