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公开(公告)号：WO2006059968A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/039961
申请日：2004-12-01
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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12.发明申请
公开(公告)号：WO2015088606A3
公开(公告)日：2015-07-30
申请号：PCT/US2014054733
申请日：2014-09-09
发明人： ROBERGE GARY D
CPC分类号： F02C3/04 , F01D13/006 , F02C3/073 , F02K3/06 , F02K3/068 , F02K3/072 , F05D2220/32 , F05D2220/323 , Y02T50/672
摘要： A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an inlet of a reverse-core gas generator, and a second portion, configured to receive air from an exit of the gas generator and direct the air forward and radially outward of the propulsor, toward the fan-tip turbine in the propulsor, thereby driving the propulsor.
摘要翻译： 一种反向堆芯涡轮风扇发动机，其包括推进器部分，所述推进器部分包括风扇和风扇叶顶涡轮，所述推进器部分构造成将空气输送到芯管，所述芯管包括设置在推进器部分的后部的第一部分以及将空气引导向尾部朝向 以及第二部分，所述第二部分构造成从所述气体发生器的出口接收空气，并将所述空气朝向所述推进器的所述风扇尖端涡轮机推进，从而驱动所述推进器。
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公开(公告)号：WO2014123796A1
公开(公告)日：2014-08-14
申请号：PCT/US2014/014367
申请日：2014-02-03
IPC分类号： F02K3/068
CPC分类号： F02C7/36 , B64D33/02 , B64D2033/0286 , F02C3/10 , F02C3/107 , F02K3/06 , F02K3/068 , F05D2220/36 , Y02T50/672
摘要： A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.
摘要翻译： 推进系统包括风扇，齿轮，被配置为驱动齿轮的涡轮，从而驱动风扇。 涡轮机具有出口点，并且在出口处限定直径（Dt）。 机舱围绕核心发动机外壳。 风扇被配置为将空气输送到限定在机舱和核心发动机壳体之间的旁路管道中。 在出口点的下游设有核心发动机排气喷嘴。 核心发动机排气喷嘴的下游最点定义在离出口一定距离处。 距离直径之比大于或等于约0.90。
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公开(公告)号：WO2013130172A1
公开(公告)日：2013-09-06
申请号：PCT/US2012/071143
申请日：2012-12-21
发明人： KUPRATIS, Daniel, B.
IPC分类号： F02K3/04
摘要： A gas turbine engine (20; 350; 380) has, in at least a first mode of operation, a core engine (26), a fan, and an auxiliary turbine engine coupled as follows. The core engine has, along a core flowpath (520), at least one compressor section (32), a combustor (34), and at least one turbine section (36, 38). The fan (24) is upstream of the core flowpath and drives air downstream along the core flowpath and along a bypass flowpath (524). The auxiliary turbine engine (80) has an axial compressor (100), a fan, a combustor, and an axial turbine. The fan has fan blades (118) and a continuation (532) of the bypass flowpath extends seguentially downstream through the axial compressor and radially outward through passageways in the blades of the fan and a continuation (530) of the core flowpath passes axially through the fan. The combustor (136) is downstream of the fan along the continuation of the bypass flowpath. The axial turbine (150) is downstream of the combustor along the continuation of the bypass flowpath and comprises at least one stage of blades (152, 154) rotating with the fan.
摘要翻译： 在至少第一操作模式中，燃气涡轮发动机（20; 350; 380）具有如下耦合的核心发动机（26），风扇和辅助涡轮发动机。 核心发动机沿着核心流路（520）具有至少一个压缩机部分（32），燃烧器（34）和至少一个涡轮部分（36,38）。 风扇（24）位于核心流路的上游，并沿着核心流路沿着旁路流路（524）驱动下游的空气。 辅助涡轮发动机（80）具有轴向压缩机（100），风扇，燃烧器和轴向涡轮机。 风扇具有风扇叶片（118），并且旁路流动路径的延续部分（532）沿着轴向压缩机逐渐向下游延伸，并且通过风扇叶片中的通道径向向外延伸，并且核心流路的延续部分（530）轴向通过 风扇。 燃烧器（136）沿着旁路流路的延续在风扇的下游。 轴向涡轮机（150）沿着旁路流动路径的延续在燃烧器的下游，并且包括与风扇一起旋转的至少一个叶片级（152,154）。
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公开(公告)号：WO2006110125A3
公开(公告)日：2007-02-22
申请号：PCT/US2004040206
申请日：2004-12-01
发明人： SUCIU GABRIEL L , ROBERGE GARY D , MERRY BRIAN
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 thereform. 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）和沿径向延伸的多个翼型件（52）。 多个翼型件可以与环形部分一体地形成。 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：WO2006060011A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040210
申请日：2004-12-01
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：WO2006060006A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040176
申请日：2004-12-01
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筒（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：WO2006060004A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040171
申请日：2004-12-01
IPC分类号： F23R3/28
摘要： A turbine engine includes an annular combustor having a combustion chamber defined between an annular outer wall and an annular inner wall. A diffuser case substantially encloses the annular outer and inner walls. A fuel nozzle extends through the diffuser case to an outlet that provides fuel to an interior chamber of the combustor. In one embodiment, front portions of the inner and outer walls curve toward one another and overlap to form an annular gap or manifold through which fuel is distributed to the combustion chamber.
摘要翻译： 涡轮发动机包括具有限定在环形外壁和环形内壁之间的燃烧室的环形燃烧器。 扩散器壳体基本上包围环形的外壁和内壁。 燃料喷嘴通过扩散器壳体延伸到向燃烧器的内部室提供燃料的出口。 在一个实施例中，内壁和外壁的前部部分彼此相对弯曲并重叠以形成环形间隙或歧管，燃料通过该间隙或歧管分配到燃烧室。
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19.发明申请
公开(公告)号：WO2006059986A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040067
申请日：2004-12-01
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 reducing 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）来消除或减少轴流式压缩机（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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公开(公告)号：WO2006059978A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/039980
申请日：2004-12-01
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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