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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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公开(公告)号：US07845157B2
公开(公告)日：2010-12-07
申请号：US11719317
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
IPC分类号： F02K3/02
CPC分类号： F02C3/107 , F02C3/073 , F02C7/36 , F02K3/068 , F05D2260/40311
摘要： A tip turbine engine (10) according to the present invention provides at least one gear (90) coupling rotation of a bypass fan (24) to an axial compressor (22), such that the axial compressor (22) is driven by rotation of the fan (24) at a rate different from than the rate of the fan. In one embodiment, the rate of rotation of the axial compressor (22) is increased relative to a rate of rotation of the fan (24). By increasing the rotation rate, the compression provided by the axial compressor is increased, while the number of stages of the axial compressor blades may be reduced. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.
摘要翻译： 根据本发明的顶端涡轮发动机（10）提供将旁路风扇（24）的旋转耦合到轴向压缩机（22）的至少一个齿轮（90），使得轴向压缩机（22）由 风扇（24）的速度与风扇的速率不同。 在一个实施例中，轴向压缩机（22）的旋转速率相对于风扇（24）的旋转速率增加。 通过提高旋转速度，由轴流式压缩机提供的压缩增加，同时可减小轴向压缩机叶片的级数。 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：US20090148292A1
公开(公告)日：2009-06-11
申请号：US11719317
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
CPC分类号： F02C3/107 , F02C3/073 , F02C7/36 , F02K3/068 , F05D2260/40311
摘要： A tip turbine engine (10) according to the present invention provides at least one gear (90) coupling rotation of a bypass fan (24) to an axial compressor (22), such that the axial compressor (22) is driven by rotation of the fan (24) at a rate different from than the rate of the fan. In one embodiment, the rate of rotation of the axial compressor (22) is increased relative to a rate of rotation of the fan (24). By increasing the rotation rate, the compression provided by the axial compressor is increased, while the number of stages of the axial compressor blades may be reduced. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.
摘要翻译： 根据本发明的顶端涡轮发动机（10）提供将旁路风扇（24）的旋转耦合到轴向压缩机（22）的至少一个齿轮（90），使得轴向压缩机（22）由 风扇（24）的速度与风扇的速率不同。 在一个实施例中，轴向压缩机（22）的旋转速率相对于风扇（24）的旋转速率增加。 通过提高旋转速度，由轴流式压缩机提供的压缩增加，同时可减小轴向压缩机叶片的级数。 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：US20090145101A1
公开(公告)日：2009-06-11
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
IPC分类号： B01D45/12
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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公开(公告)号：US20090155079A1
公开(公告)日：2009-06-18
申请号：US11719603
申请日：2004-12-01
申请人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
发明人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
CPC分类号： F02K3/068 , F01D5/025 , F01D5/34 , F02C3/067 , F02C3/073 , Y02T50/671 , Y10T29/49321
摘要： Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.
摘要翻译： 作为示例，关于具有多个环形压缩机转子翼型组件（120）的轴向压缩机来描述改进的环形部件和用于将环形部件组装到涡轮发动机中的改进方法。 每个压缩机转子翼型组件包括环形转子部分（122），从其轴向延伸的间隔部分（124）和从其径向延伸的多个翼型件（52）。 多个翼型件可以与环形部分整体形成。 压缩机转子翼型件组件依次堆叠在中心连接件（134）或外圆环上。 一个压缩机转子翼型组件（120a）的间隔部分邻接邻近的压缩机转子翼型组件（120b）的环形转子部分，以将它们彼此保持在中心连接的外圆环上。 通过依次堆叠压缩机转子叶片组件然后保持它们，可以消除典型的分体式壳体，凸缘和转子螺栓。
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公开(公告)号：US20080087023A1
公开(公告)日：2008-04-17
申请号：US11577595
申请日：2004-12-01
申请人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
发明人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
摘要： A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support plane (P), which is perpendicular to an engine centerline (A). The shaft (60) is rotationally fixed, coaxial with the engine centerline (A), and structurally supported by the engine support structure (12) such that a load borne by the shaft (60) is transferred along the engine support plane.
摘要翻译： 根据本发明的顶端涡轮发动机（10）包括用于从发动机支撑平面（P）悬挂负载轴的发动机支撑结构（12）。 发动机支撑结构（12）限定垂直于发动机中心线（A）的发动机支撑平面（P）。 轴（60）旋转地固定，与发动机中心线（A）同轴，并且由发动机支撑结构（12）结构地支撑，使得由轴（60）承载的负载沿发动机支撑平面传递。
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公开(公告)号：US08087885B2
公开(公告)日：2012-01-03
申请号：US11719603
申请日：2004-12-01
申请人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
发明人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
IPC分类号： F01D5/06
CPC分类号： F02K3/068 , F01D5/025 , F01D5/34 , F02C3/067 , F02C3/073 , Y02T50/671 , Y10T29/49321
摘要： Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.
摘要翻译： 作为示例，关于具有多个环形压缩机转子翼型组件（120）的轴向压缩机来描述改进的环形部件和用于将环形部件组装到涡轮发动机中的改进方法。 每个压缩机转子翼型组件包括环形转子部分（122），从其轴向延伸的间隔部分（124）和从其径向延伸的多个翼型件（52）。 多个翼型件可以与环形部分整体形成。 压缩机转子翼型件组件依次堆叠在中心连接件（134）或外圆环上。 一个压缩机转子翼型件组件（120a）的间隔部分邻接相邻的压缩机转子翼型组件（120b）的环形转子部分，以将其彼此保持在中心连接的外圆环上。 通过依次堆叠压缩机转子叶片组件然后保持它们，可以消除典型的分体式壳体，凸缘和转子螺栓。
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公开(公告)号：US08033094B2
公开(公告)日：2011-10-11
申请号：US11577595
申请日：2004-12-01
申请人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
发明人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
IPC分类号： F02K3/02
摘要： A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support plane (P), which is perpendicular to an engine centerline (A). The shaft (60) is rotationally fixed, coaxial with the engine centerline (A), and structurally supported by the engine support structure (12) such that a load borne by the shaft (60) is transferred along the engine support plane.
摘要翻译： 根据本发明的顶端涡轮发动机（10）包括用于从发动机支撑平面（P）悬挂负载轴的发动机支撑结构（12）。 发动机支撑结构（12）限定垂直于发动机中心线（A）的发动机支撑平面（P）。 轴（60）旋转地固定，与发动机中心线（A）同轴，并且由发动机支撑结构（12）结构地支撑，使得由轴（60）承载的负载沿发动机支撑平面传递。
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9.发明申请REMOTE ENGINE FUEL CONTROL AND ELECTRONIC ENGINE CONTROL FOR TURBINE ENGINE 审中-公开用于涡轮发动机的远程发动机燃油控制和电子发动机控制公开(公告)号：US20090145105A1
公开(公告)日：2009-06-11
申请号：US11719470
申请日：2004-12-01
申请人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
发明人： Gabriel L. Suciu , Gary D. Roberge , Brian Merry
IPC分类号： F02C9/26
摘要： A controller is mounted remotely from a turbine engine and provided with an independent power source (120, 138). The controller may be an engine controller (112) generating control signals based upon user inputs and sensor inputs, or a fuel controller (114) controlling a supply of fuel to the turbine engine (10), or both. Each controller includes a power source independent of the turbine engine, i.e. the power source supplies power even when the turbine and fan of the turbine engine (10) are not turning. A single wire harness and a single fuel line (118) connect the engine controller (112) and the fuel controller (114) to the turbine engine (10).
摘要翻译： 控制器从涡轮发动机远程安装并且设置有独立的电源（120,138）。 控制器可以是基于用户输入和传感器输入产生控制信号的发动机控制器（112），或者控制向涡轮发动机（10）供应燃料的燃料控制器（114），或两者。 每个控制器包括独立于涡轮发动机的电源，即即使当涡轮发动机（10）的涡轮机和风扇不转动时，电源也能够供电。 单个线束和单个燃料管线（118）将发动机控制器（112）和燃料控制器（114）连接到涡轮发动机（10）。
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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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