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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
Applicant: Gabriel Suciu , Brian Merry , Michael E. McCune
Inventor： Gabriel Suciu , Brian Merry , Michael E. McCune
IPC: F02C1/06
CPC classification number: F02C3/08 , F02C3/073 , F02C3/107 , F02C7/36 , F02K3/068 , F04D25/045 , F05D2260/40311 , F16H48/10
Abstract: 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.
Abstract translation: 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
Applicant: Gabriel Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
Inventor： Gabriel Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
IPC: F01D9/00
Abstract: 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.
Abstract translation: 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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13.发明申请公开(公告)号：US20070292270A1
公开(公告)日：2007-12-20
申请号：US11718522
申请日：2004-12-01
Applicant: Gabriel Suciu , James Norris , Craig Nordeen
Inventor： Gabriel Suciu , James Norris , Craig Nordeen
CPC classification number: F02C3/073 , F01D5/225 , F01D5/3007 , F02C3/08 , F02K3/068 , F05D2260/30 , Y10T29/49321
Abstract: A tip turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. Assembly of a multitude of turbine blade clusters to a diffuser includes axial installation and radial rotation. The clusters are axially installed, then rotated toward a radial stop in a direction which will maintain each cluster against the radial stop during operation of the fan-turbine rotor assembly. A multitude of turbine rotor ring stages may also be locked together to future increase the rigidity of the turbine
Abstract translation: 顶端涡轮发动机包括包括一个或多个涡轮机环形转子的风扇 - 涡轮机转子组件。 每个涡轮环由多个涡轮机叶片组装配。 将多个涡轮机叶片组装配到扩散器包括轴向安装和径向旋转。 簇被轴向地安装，然后沿着在风扇 - 涡轮机转子组件的操作期间将每个簇抵靠径向停止件保持的方向朝向径向止动件旋转。 许多涡轮机转子环级也可以被锁定在一起以便未来增加涡轮机的刚性
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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
Applicant: Kevin J. Cummings , Christopher G. Demers , James C. Hodgson , Gabriel Suciu , Brian Merry
Inventor： Kevin J. Cummings , Christopher G. Demers , James C. Hodgson , Gabriel Suciu , Brian Merry
IPC: F01D25/14
CPC classification number: F04D19/02 , F01D17/105 , F01D25/162 , F04D27/0215 , F04D27/023 , F04D29/545 , Y10T29/49323
Abstract: 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.
Abstract translation: 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：US20060251508A1
公开(公告)日：2006-11-09
申请号：US11122368
申请日：2005-05-05
Applicant: James Norris , Craig Nordeen , Gary Roberge , Gabriel Suciu
Inventor： James Norris , Craig Nordeen , Gary Roberge , Gabriel Suciu
IPC: F04D31/00
CPC classification number: F01D11/005 , F02C3/073 , F02K3/06 , F02K3/068 , Y02T50/672
Abstract: A fan-turbine rotor hub includes an outer periphery scalloped by a multitude of elongated openings. Each elongated opening defines an inducer receipt section to receive an inducer section and a hollow fan blade section. An inducer exit from each inducer section is located adjacent a core airflow passage within each fan blade section to provide communication therebetween. A seal is located between an inner fan blade mount and a blade receipt section to minimize airflow leakage between the inducer exit and the core airflow passage.
Abstract translation: 风扇涡轮转子毂包括由多个细长开口扇形的外周。 每个细长的开口限定了一个诱导器接收部分，以便接纳一个导流部分和一个中空的风扇叶片部分。 每个导流部分的导流器出口位于每个风扇叶片部分内的核心气流通道附近，以在它们之间提供连通。 密封件位于内部风扇叶片安装件和叶片接收部分之间，以最小化引导器出口和芯气流通道之间的气流泄漏。
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Patent Agency Ranking
公开(公告)号：US07845157B2
公开(公告)日：2010-12-07
申请号：US11719317
申请日：2004-12-01
Applicant: Gabriel Suciu , Gary D. Roberge , Brian Merry
Inventor： Gabriel Suciu , Gary D. Roberge , Brian Merry
IPC: F02K3/02
CPC classification number: F02C3/107 , F02C3/073 , F02C7/36 , F02K3/068 , F05D2260/40311
Abstract: 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.
Abstract translation: 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
Applicant: Gabriel Suciu , Gary D. Roberge , Brian Merry
Inventor： Gabriel Suciu , Gary D. Roberge , Brian Merry
CPC classification number: F02C3/107 , F02C3/073 , F02C7/36 , F02K3/068 , F05D2260/40311
Abstract: 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.
Abstract translation: 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
Applicant: Gabriel Suciu , Gary D. Roberge , Brian Merry
Inventor： Gabriel Suciu , Gary D. Roberge , Brian Merry
IPC: B01D45/12
Abstract: 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.
Abstract translation: 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：US20090071121A1
公开(公告)日：2009-03-19
申请号：US11719224
申请日：2004-12-01
Applicant: Gabriel Suciu , Brian Merry , Michael E. McCune
Inventor： Gabriel Suciu , Brian Merry , Michael E. McCune
CPC classification number: F02C3/08 , F02C3/073 , F02C3/107 , F02C7/36 , F02K3/068 , F04D25/045 , F05D2260/40311 , F16H48/10
Abstract: 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.
Abstract translation: 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
Applicant: Gabriel Suciu , Brian Merry
Inventor： Gabriel Suciu , Brian Merry
IPC: F01D25/24
Abstract: 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).
Abstract translation: 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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