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公开(公告)号：US07921636B2
公开(公告)日：2011-04-12
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： F02K3/02
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：US20080092552A1
公开(公告)日：2008-04-24
申请号：US11718519
申请日：2004-12-01
申请人： Gabriel Suciu , Lawrence Portlock , Brian Merry
发明人： Gabriel Suciu , Lawrence Portlock , Brian Merry
CPC分类号： F02C3/073 , F01D5/022 , F01D25/183 , F02C7/32 , F02K3/068 , F05D2260/40311
摘要： A hydraulic seal (170) for a tip turbine engine includes an inner radial flange (171) and an outer radial flange (172). The inner radial flange (171) rotates relative the outer radial seal section and the planet carrier face (94) to prevent lubrication from entering into the air flow streams within the engine without additional engine assembly procedures.
摘要翻译： 用于顶端涡轮发动机的液压密封件（170）包括内径向凸缘（171）和外径向凸缘（172）。 内部径向凸缘（171）相对于外部径向密封部分和行星架面（94）旋转，以防止润滑进入发动机内的空气流动流，而无需额外的发动机组装程序。
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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：US20090071121A1
公开(公告)日：2009-03-19
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
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：US20080095618A1
公开(公告)日：2008-04-24
申请号：US11720536
申请日：2004-12-01
申请人： Gabriel Suciu , Brian Merry
发明人： Gabriel Suciu , Brian Merry
IPC分类号： F01D25/24
摘要： A tip turbine engine assembly according to the present invention includes a load bearing engine support structure (12). The engine support structure (12) includes an engine support plane (P) that is substantially perpendicular to an engine centerline (A) and first rotationally fixed member (50) disposed about the engine centerline (A) and cantilevered from the engine support plane (P). A support member extends radially outward from the first rotationally fixed member (50) and structurally supports a second rotationally fixed member (58) that is coaxial with the first rotationally fixed member. A rotor is mounted on the first rotationally fixed member and rotates about the engine centerline (A).
摘要翻译： 根据本发明的顶端涡轮发动机组件包括负载发动机支撑结构（12）。 发动机支撑结构（12）包括基本上垂直于发动机中心线（A）的发动机支撑平面（P）和围绕发动机中心线（A）设置并从发动机支撑平面悬臂的第一旋转固定构件（50） P）。 支撑构件从第一旋转固定构件（50）径向向外延伸，并且结构地支撑与第一旋转固定构件同轴的第二旋转固定构件（58）。 转子安装在第一旋转固定构件上并围绕发动机中心线（A）旋转。
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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：US20060248900A1
公开(公告)日：2006-11-09
申请号：US11122336
申请日：2005-05-05
申请人： Gabriel Suciu , Brian Merry
发明人： Gabriel Suciu , Brian Merry
IPC分类号： F02C6/00
CPC分类号： F02C7/36 , F02C7/32 , Y02T50/671 , Y10S74/05
摘要： Provided is an accessory gearbox for a gas turbine engine that contributes minimally to engine weight and complexity. An accessory gearbox comprises a stationary frame that is circumferentially disposed about a central longitudinal axis of the engine. The frame includes a forward-directed axial face and a rearward-directed axial face for fastening the frame to the engine. A central bore accepts a rotational driving means and an outermost rim circumscribes the outer diameter of the frame. A compartment is located between the bore and the rim. At least one primary accessory is mounted to a face and proximate the compartment, remotely engaging the driving means and able to be driven concurrently therewith.
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公开(公告)号：US08757959B2
公开(公告)日：2014-06-24
申请号：US11718420
申请日：2004-12-01
申请人： Gabriel L. Suciu , Brian Merry , Lawrence Portlock
发明人： Gabriel L. Suciu , Brian Merry , Lawrence Portlock
IPC分类号： F01D25/20
摘要： A non-rotating compartment along an engine centerline of a tip turbine engine is defined between an inner support housing, an outer support housing and an aft housing. The non-rotating compartment provides a space that may be utilized for a multitude of engine accessories and components including an engine lubricating fluid system.
摘要翻译： 沿着顶部涡轮发动机的发动机中心线的非旋转舱被限定在内部支撑壳体，外部支撑壳体和后部壳体之间。 非旋转隔室提供可用于多个发动机附件和部件的空间，包括发动机润滑流体系统。
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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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