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公开(公告)号：US08177527B2
公开(公告)日：2012-05-15
申请号：US12068378
申请日：2008-02-06
申请人： Masatsugu Ishiba
发明人： Masatsugu Ishiba
CPC分类号： B64C11/001 , B64C29/0016 , F02C3/073 , F02K3/068 , F04D25/045
摘要： At the time of an operation, high-pressure air 8 fed through an inlet 6 passes a stator vane 4 within a duct 15, so as to adjust its flow, and is supplied to a tip turbine rotor vane 3. The tip turbine rotor vane 3 is supplied with the high-pressure air 8 from the exhaust side 17 toward the intake side 16, so as to drive an upper fan 2 and a lower fan 14 to rotate in the same direction. This can shorten the distance H from a rotation surface 12 of the upper fan 2 to the end part of a fan casing 1 on the intake side 16, and thus reduce an area where a negative pressure occurs when receiving a crosswind 9, thereby lowering an external force 11 caused by the negative pressure.
摘要翻译： 在操作时，通过入口6供给的高压空气8通过管道15内的定子叶片4，以便调节其流动，并将其供应到顶端涡轮机转子叶片3.顶端涡轮机转子叶片 3从排气侧17向吸入侧16供给高压空气8，驱动上部风扇2和下部风扇14向同一方向旋转。 这可以缩短从上风扇2的旋转面12到吸入侧16的风扇壳体1的端部的距离H，从而在接收侧风9时减小发生负压的区域，从而降低 外力11由负压引起。
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公开(公告)号：US20120111018A1
公开(公告)日：2012-05-10
申请号：US13334249
申请日：2011-12-22
申请人： James W. Norris , Craig A. Nordeen
发明人： James W. Norris , Craig A. Nordeen
CPC分类号： F04D25/045 , F01D5/022 , F02C3/064 , F02C3/073 , F02C7/36 , F02K3/025 , F02K3/068 , F05D2260/40311
摘要： A tip turbine engine provides increased efficiency while eliminating or reducing the number of axial compressor stages by moving the core airflow inlet aft of the fan. As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers in the hollow fan blades for further, centrifugal compression.
摘要翻译： 尖端涡轮发动机通过移动风扇后部的核心气流入口来提高效率，同时消除或减少轴向压缩机级数。 结果，进入核心气流入口的核心气流是已经处于增加压力的风扇排气。 风扇排气的一部分被径向向内引导，然后轴向前进，然后径向向外通过中空风扇叶片中的压缩机室，用于进一步的离心压缩。
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公开(公告)号：US08096753B2
公开(公告)日：2012-01-17
申请号：US11719587
申请日：2004-12-01
申请人： James W. Norris , Craig A. Nordeen
发明人： James W. Norris , Craig A. Nordeen
IPC分类号： F01D15/12
CPC分类号： F04D25/045 , F01D5/022 , F02C3/064 , F02C3/073 , F02C7/36 , F02K3/025 , F02K3/068 , F05D2260/40311
摘要： A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers (72) in the hollow fan blades (28) for further, centrifugal compression.
摘要翻译： 顶端涡轮发动机（10）和操作发动机的方法通过移动风扇（24）后部的空气流入口（27）来消除或教导轴流式压缩机（122）级的数量，提高了效率。 结果，进入核心气流入口的核心气流是已经处于增加压力的风扇排气。 风扇排气的一部分被径向向内引导，然后轴向向前，然后径向向外通过中空风扇叶片（28）中的压缩机室（72）进一步进行离心压缩。
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84.发明授权公开(公告)号：US08061968B2
公开(公告)日：2011-11-22
申请号：US11719892
申请日：2004-12-01
IPC分类号： F01D1/24
摘要： A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77) couples the rotation of the turbine (32) and fan (28) to an axial compressor rotor (46) having a plurality of inner compressor airfoils (52). In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils. The outer compressor airfoils (54) are formed on a plurality of outer airfoil assemblies (56) each having an arcuate substrate (58) from which the outer compressor airfoils (54) extend. Each of the outer compressor airfoil assemblies (56) includes more than one axially-spaced stage of outer compressor airfoils (54). For assembly, the outer compressor airfoil assemblies (56) are moved toward the axial compressor rotor (46) and then inserted into the compressor case (50).
摘要翻译： 顶端涡轮发动机（10）提供具有压缩机壳体（50）的轴向压缩机（22），径向向内延伸有多个外部压缩机翼型件（54）。 压缩机壳体（50）由涡轮机（32）和风扇（28）的旋转直接驱动，而至少一个齿轮（77）将涡轮机（32）和风扇（28）的旋转与轴向压缩机 转子（46）具有多个内部压缩机翼型件（52）。 以这种方式，轴向压缩机转子（46）沿与外压缩机翼片（54）的方向相反的方向被驱动，从而增加由压缩机提供的压缩而不增加翼型件的数量。 外压缩机翼片（54）形成在多个外翼型组件（56）上，每个外翼型组件（56）具有弓形基板（58），外压缩机翼型件（54）从该外形翼片组件延伸。 每个外部压缩机翼型组件（56）包括多于一个轴向隔开的外压缩机翼片（54）。 为了组装，外压缩机翼型组件（56）朝向轴向压缩机转子（46）移动，然后插入压缩机壳体（50）中。
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公开(公告)号：US07988087B1
公开(公告)日：2011-08-02
申请号：US08634594
申请日：1996-04-25
IPC分类号： B64C29/00
CPC分类号： B64C29/0058 , B64C15/12 , B64C15/14 , B64D33/04 , F02K1/006 , F02K1/008 , F02K1/1207 , F02K3/068
摘要： A nozzle arrangement for a VTOL or STOVL aircraft having an airframe mounted lift system comprises a hinged deflector door pivotally mounted on the underside of the airframe for exhaust efflux deflection. The door is movable about its axis to vector impinging exhaust gases rearwards during the transition between vertical and horizontal flight, and in addition comprises a pair of lateral sidewalls which are movable in the plane of the door to direct the exhaust efflux sideways for improved aircraft yaw control.
摘要翻译： 用于具有机身安装的升降系统的VTOL或STOVL飞机的喷嘴装置包括枢转地安装在机身的下侧上的用于排气流出偏转的铰接偏转器门。 门可以围绕其轴线移动，以在垂直和水平飞行之间的过渡期间向后冲击排气，并且还包括一对侧壁，其可在门的平面中移动以引导排气流向侧向以改善飞行器偏航 控制。
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公开(公告)号：US07976273B2
公开(公告)日：2011-07-12
申请号：US11720536
申请日：2004-12-01
申请人： Gabriel L. Suciu , Brian Merry
发明人： Gabriel L. Suciu , Brian Merry
IPC分类号： F02K3/02
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：US07976272B2
公开(公告)日：2011-07-12
申请号：US11719911
申请日：2004-12-01
IPC分类号： F01D25/12
CPC分类号： F16K7/10 , F01D5/022 , F01D17/14 , F01D17/141 , F01D17/143 , F02C3/073 , F02C3/14 , F02C6/08 , F02C9/18 , F02K3/068 , F04D27/0215 , F04D27/023 , F05D2300/501 , F16K7/123 , F16K31/1266
摘要： A compressor for a turbine engine includes an inflatable bleed valve that selectively bleeds core airflow from the compressor. The bleed valve has an inlet leading from the compressor and a passageway leading from the inlet. An inflatable valve selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve.
摘要翻译： 一种用于涡轮发动机的压缩机包括一个可充气放气阀，其选择性地从压缩机中排出核心气流。 排放阀具有从压缩机引出的入口和从入口通过的通道。 充气阀基于向可充气阀的受控供应的高压空气选择性地阻塞通道。 高压空气的供应可以是从入口下游到排放阀的压缩空气流。
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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：US20090178386A1
公开(公告)日：2009-07-16
申请号：US12013431
申请日：2008-01-12
申请人： Humberto W. Sachs
发明人： Humberto W. Sachs
IPC分类号： F02K3/02
CPC分类号： F02K3/068 , F02C3/165 , F02K3/06 , F05D2250/25 , F05D2250/314 , F05D2250/51 , F05D2250/52 , Y02T50/671
摘要： The invention is a novel aircraft propulsion system architecture that delivers thrust at minimum fuel consumption rates with the side benefits of noise and pollution emission abatement. The invention implements three technologies: a. Unique turbine nozzle design allowing for a cooling cycle, thus increasing its thermal efficiency. b. Specific jet-drive design propelling the fan blades allowing for power amplification. At any given shaft velocity, the output torque of a machine is proportional to shaft power. Jet-driven torque is insensitive to velocity. For nozzle velocities greater than 550 fps, there is power amplification (et propulsion principle). c. Specific exhaust and waste heat regeneration design increasing the fanjet thrust with no additional fuel consumption. This aircraft propulsion system invention is henceforth called APS.
摘要翻译： 本发明是一种新颖的飞机推进系统架构，其以最小的燃料消耗率提供推力，具有噪声和污染物排放减少的副作用。 本发明实现三种技术：a。 独特的涡轮喷嘴设计允许冷却循环，从而提高其热效率。 b。 特定的喷射驱动设计推动了风扇叶片，从而实现功率放大。 在任何给定的轴速度下，机器的输出扭矩与轴功率成比例。 喷射驱动扭矩对速度不敏感。 对于大于550fps的喷嘴速度，存在功率放大（et推进原理）。 C。 具体的排气和废热再生设计增加了风扇喷气推力，无需额外的燃油消耗。 这种飞机推进系统的发明从此称为APS。
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90.发明申请COUNTER-ROTATING COMPRESSOR CASE AND ASSEMBLY METHOD FOR TIP TURBINE ENGINE 有权逆向旋转压缩机壳体和TIP涡轮发动机的组装方法公开(公告)号：US20090162187A1
公开(公告)日：2009-06-25
申请号：US11719892
申请日：2004-12-01
IPC分类号： F01D1/24
摘要： A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77) couples the rotation of the turbine (32) and fan (28) to an axial compressor rotor (46) having a plurality of inner compressor airfoils (52). In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils. The outer compressor airfoils (54) are formed on a plurality of outer airfoil assemblies (56) each having an arcuate substrate (58) from which the outer compressor airfoils (54) extend. Each of the outer compressor airfoil assemblies (56) includes more than one axially-spaced stage of outer compressor airfoils (54). For assembly, the outer compressor airfoil assemblies (56) are moved toward the axial compressor rotor (46) and then inserted into the compressor case (50).
摘要翻译： 顶端涡轮发动机（10）提供具有压缩机壳体（50）的轴向压缩机（22），径向向内延伸有多个外部压缩机翼型件（54）。 压缩机壳体（50）由涡轮机（32）和风扇（28）的旋转直接驱动，而至少一个齿轮（77）将涡轮机（32）和风扇（28）的旋转与轴向压缩机 转子（46）具有多个内部压缩机翼型件（52）。 以这种方式，轴向压缩机转子（46）沿与外压缩机翼片（54）的方向相反的方向被驱动，从而增加由压缩机提供的压缩而不增加翼型件的数量。 外压缩机翼片（54）形成在多个外翼型组件（56）上，每个外翼型组件（56）具有弓形基板（58），外压缩机翼型件（54）从该外形翼片组件延伸。 每个外部压缩机翼型组件（56）包括多于一个轴向隔开的外压缩机翼片（54）。 为了组装，外压缩机翼型组件（56）朝向轴向压缩机转子（46）移动，然后插入压缩机壳体（50）中。
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