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公开(公告)号：US07854112B2
公开(公告)日：2010-12-21
申请号：US11719477
申请日：2004-12-01
申请人： Gary D. Roberge
发明人： Gary D. Roberge
IPC分类号： F02K3/02
摘要： A transition duct (112) is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine (10) from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of the transition duct. The transition duct incorporates a perimeter slot (124) providing cooling to the duct outer wall and attached components. The variable vanes (120) are installed to vector the exhaust gases. This allows the aircraft to decelerate, hover or accelerate in the forward direction by commanding the position of the variable vanes. One potential application of the tip turbine engine is for vertical installations in aircraft.
摘要翻译： 在涡轮发动机的出口处设置过渡管道（112）。 过渡管道将尖端涡轮发动机（10）的出口从圆形过渡到矩形。 过渡管道还在过渡管道的出口处提供多个可变叶片。 过渡管道包括为管道外壁和附接部件提供冷却的周边槽（124）。 可变叶片（120）被安装成对废气进行传播。 这允许飞机通过指示可变叶片的位置来向前方向减速，悬停或加速。 尖端涡轮发动机的一个潜在应用是飞机中的垂直安装。
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公开(公告)号：US07685805B2
公开(公告)日：2010-03-30
申请号：US11561601
申请日：2006-11-20
申请人： Daniel T. Alecu
发明人： Daniel T. Alecu
IPC分类号： F02K3/04
CPC分类号： F02K3/068 , F02C3/08 , F02K1/28 , F02K1/30 , F02K1/50 , F02K3/06 , F05D2250/711 , F05D2250/712
摘要： The arrangement comprises a fan by-pass duct located within the nacelle and having an inlet and an outlet. The outlet is generally oriented substantially radially and at an intermediary location along the nacelle. The nacelle has an aft section with an initially convex and substantially outwardly extending surface adjacent to the outlet of the fan by-pass duct. The surface of the aft section decreases in curvature and becomes concave towards a rear end of the engine.
摘要翻译： 该装置包括位于机舱内并具有入口和出口的风扇旁路管道。 出口通常基本上径向定位并且沿着机舱的中间位置。 机舱具有一个后部段，其具有与风扇旁路管道的出口相邻的初始凸起并且基本上向外延伸的表面。 后段的表面曲率减小，朝向发动机的后端变为凹。
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公开(公告)号：US20100037623A1
公开(公告)日：2010-02-18
申请号：US12189908
申请日：2008-08-12
摘要： A by-pass turbofan gas turbine engine, comprises: a by-pass fan with a by-pass fan outlet; a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet; a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct with a by-pass duct inlet coupled to the by-pass fan outlet and a by-pass duct outlet; an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet; a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet; a generally annular recuperator with a cool side inlet coupled to the downstream compressor outlet, a cool side outlet, a warm side inlet and a warm side outlet; a generally annular combustor with a combustor inlet coupled to the recuperator cool side outlet and a combustor outlet; a radial turbine with a radial turbine inlet coupled to the combustor inlet and a turbine outlet coupled to the recuperator warm side inlet; at least one exhaust nozzle with an exhaust nozzle inlet coupled to the recuperator warm side outlet and an exhaust nozzle outlet that discharges into the by-pass duct between the by-pass duct inlet and outlet; and a propelling nozzle coupled to the by-pass duct outlet.
摘要翻译： 旁通涡轮风扇燃气涡轮发动机包括：具有旁路风扇出口的旁路风扇; 大致环形的核心发动机管道，其具有联接到旁路风扇出口的核心发动机管道入口和核心发动机管道出口; 大致环形的旁路管道，其与核心发动机管道大体上具有同轴的关系，其中旁路管道入口连接到旁路风扇出口和旁路管道出口; 上游轴向压缩机，其具有联接到所述核心发动机管道出口的轴向上游压缩机入口和轴向上游压缩机出口; 下游径向压缩机，其具有联接到上游压缩机出口的轴向下游压缩机入口和径向下游压缩机出口; 一个大体上环形的换热器，其具有连接到下游压缩机出口的冷侧入口，一个冷侧出口，一个暖侧入口和一个暖侧出口; 大致环形的燃烧器，其燃烧器入口连接到换热器冷侧出口和燃烧器出口; 具有联接到燃烧器入口的径向涡轮机入口和联接到换热器暖侧入口的涡轮机出口的径向涡轮机; 至少一个排气喷嘴，其具有联接到换热器暖侧出口的排气喷嘴入口和排出到旁路管道入口和出口之间的旁路管道的排气喷嘴出口; 以及联接到旁路管道出口的推进喷嘴。
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公开(公告)号：US20090304504A1
公开(公告)日：2009-12-10
申请号：US11497304
申请日：2006-08-02
申请人： Masatsugu Ishiba
发明人： Masatsugu Ishiba
IPC分类号： F04D29/54
CPC分类号： B64C11/001 , B64C27/08 , B64C27/20 , B64C29/0016 , B64C39/026 , F02C3/073 , F02K3/068 , F04D29/526 , Y02T50/671 , Y10S415/914
摘要： A ducted fan includes a fan that generates an airflow that flows substantially parallel with the axis of the rotating shaft of the fan; a duct, arranged around the fan, that extends in the direction of the rotating shaft of the fan and includes an airflow inlet defined by the upstream end and an airflow outlet defined by the downstream end, and that has a ramp portion formed in the inner face of the airflow inlet; an airflow guide portion, provided at the airflow outlet, that introduces air from outside of the duct to a position downstream of the airflow outlet; and a negative-pressure forming portion, provided at the downstream end of the airflow guide portion. The negative-pressure forming portion generates a negative pressure near the downstream end of the airflow guide portion when air passes by the negative-pressure forming portion.
摘要翻译： 管道风扇包括：风扇，其产生与风扇的旋转轴的轴线基本平行的气流; 围绕风扇布置的管道，其沿着风扇的旋转轴的方向延伸，并且包括由上游端限定的气流入口和由下游端限定的气流出口，并且具有形成在内部的斜坡部分 气流入口面; 设置在气流出口处的空气引导部，其将空气从管道外部引入到气流出口下游的位置; 以及设置在气流引导部的下游端的负压形成部。 当空气通过负压形成部分时，负压形成部分在气流引导部分的下游端附近产生负压。
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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：US20090145136A1
公开(公告)日：2009-06-11
申请号：US11719589
申请日：2004-12-01
申请人： James W. Norris , Craig A. Nordeen , Gary Roberge
发明人： James W. Norris , Craig A. Nordeen , Gary Roberge
IPC分类号： F02C3/04
CPC分类号： F02C3/14 , F01D5/022 , F02C3/067 , F02C3/073 , F02K3/068 , F02K3/072 , F05D2260/40311 , Y02T50/673
摘要： A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery of a first fan (24a), such that the first fan is rotatably driven by the first turbine (32a). The second turbine (32b) is mounted at an outer periphery of a second fan (24b), and is rotatably driven by the high-energy gas stream. In one embodiment, the first turbine (32a) rotatably drives a plurality of stages of first compressor blades (54) in an axial compressor (22) in a first rotational direction, while the second turbine (32b) rotatably drives a plurality of stages of second compressor blades (52) in the axial compressor (22) in a second rotational direction opposite the first. By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced. Other variations are described in additional embodiments.
摘要翻译： 顶端涡轮发动机（10）提供由可产生高能气流的燃烧器（30）可旋转地驱动的第一和第二涡轮机（32）。 第一涡轮（32）安装在第一风扇（24a）的外周，使得第一风扇由第一涡轮机（32a）旋转驱动。 第二涡轮（32b）安装在第二风扇（24b）的外周，由高能气流旋转驱动。 在一个实施例中，第一涡轮机（32a）以第一旋转方向可旋转地驱动轴向压缩机（22）中的多级第一压缩机叶片（54），而第二涡轮（32b）可旋转地驱动多个级 第二压缩机叶片（52）在轴向压缩机（22）中沿与第一压缩机相反的第二旋转方向。 通过以相反的方向旋转地驱动压缩机叶片的交替级，轴流式压缩机（22）的效率提高和/或压缩机叶片的级数可以减少。 在另外的实施例中描述了其它变型。
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公开(公告)号：US20080093174A1
公开(公告)日：2008-04-24
申请号：US11718429
申请日：2004-12-01
申请人： Gabriel Suciu , Brian Merry
发明人： Gabriel Suciu , Brian Merry
摘要： A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters the tailcone section through an annular tailcone exhaust nozzle entrance to transfer thermal energy into the combined airflow out of the engine to recover thrust loss ducted from the fan bypass stream.
摘要翻译： 液体 - 空气热交换器从发动机润滑流体系统中提取热能。 液体 - 空气热交换器位于尾部部分内，并且与通过环形尾气排气喷嘴入口进入尾部部分的风扇旁路气流的一部分连通，以将热能传递到从发动机外部的组合气流中以回收 从风扇旁路流引导的推力损失。
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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：US20080014078A1
公开(公告)日：2008-01-17
申请号：US11720083
申请日：2004-12-01
申请人： Gabriel Suciu , Gary Roberge
发明人： Gabriel Suciu , Gary Roberge
IPC分类号： F01D25/14
CPC分类号： F02C3/045 , F01D5/022 , F01D25/12 , F01D25/14 , F02C3/073 , F02C7/18 , F02K3/068 , Y02T50/675
摘要： A tip turbine engine (10) includes a combustor (30) radially outward of a fan. In order to reduce the heat transfer from the combustor and the high-energy gas stream generated by the combustor, a cold air ejector (38) radially outward of the combustor extends from a forward end of the nacelle (12) to a point rearward of the combustor and an exhaust mixer (110). The cold air ejector includes an annular inlet (17) at the forward end of the nacelle. The cold air ejector draws air over the outer engine case (39) to provide a boundary between the nacelle and the hot outer engine case. The layer of air being pulled past the engine case ejects the heat, thereby preventing the heat from escaping into the nacelle or engine bay.
摘要翻译： 顶端涡轮发动机（10）包括在风扇的径向外侧的燃烧器（30）。 为了减少来自燃烧器的热传递和由燃烧器产生的高能气流，从燃烧器径向向外的冷空气喷射器（38）从机舱（12）的前端延伸到 燃烧器和排气混合器（110）。 冷空气喷射器包括在机舱前端的环形入口（17）。 冷空气喷射器将空气吸引到外部发动机壳体（39）上，以提供机舱和热外部发动机壳体之间的边界。 被拉动通过发动机舱的空气层排出热量，从而防止热量逸出到机舱或发动机舱中。
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公开(公告)号：US06884021B2
公开(公告)日：2005-04-26
申请号：US10401669
申请日：2003-03-31
申请人： Yoshio Saito
发明人： Yoshio Saito
摘要： This invention provides a single cascade multistage turbine that has a compact turbine structure having only a single cascade, and enables power to be extracted efficiently in the same way as a multistage turbine having multistage rotor vanes. The working fluid supplied through the supply duct 3 flows on one side of the single cascade of rotor vanes 2 to one part of the circumference direction of the rotor vanes 2, and after passing through the rotor vanes 2 it passes through the circulation ducts 4a and 4b and returns to the former side of the rotor vanes 2. The circulation ducts 4a and 4b consist of exhaust duct members 6a and 6b, return duct members 7a and 7b, and inflow duct members 8a and 8b. Using the circulation ducts 4a and 4b this circulation process is repeated at least once whereby the working fluid is again passed through the rotor vanes 2 at a slightly different position in the circumferential direction of the rotor vanes 2. Each time the working fluid is passed through the rotor vanes 2, the energy contained in the fluid can be efficiently extracted as torque of the rotor vanes 2.
摘要翻译： 本发明提供了具有仅具有单个级联的紧凑型涡轮机结构的单级联多级涡轮机，并且能够以与具有多级转子叶片的多级涡轮机相同的方式有效地提取功率。 通过供给管道3供给的工作流体在转子叶片2的单级联的一侧流到转子叶片2的圆周方向的一部分，在通过转子叶片2后，通过循环管道4a 并且返回到转子叶片2的前一侧。 循环管道4a和4b由排气管道构件6a和6b，返回管道构件7a和7b以及流入管道构件8a和8b构成。 使用循环管道4a和4b，该循环过程重复至少一次，从而工作流体在转子叶片2的周向方向上稍微不同的位置再次通过转子叶片2。 每当工作流体通过转子叶片2时，包含在流体中的能量可以作为转子叶片2的转矩被有效地提取。
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