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公开(公告)号：US20090071162A1
公开(公告)日：2009-03-19
申请号：US11719221
申请日：2004-12-01
CPC分类号： F02C3/073 , F02C3/14 , F02K3/068 , F05D2250/311
摘要： A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34). In the combustor, the core airflow is received generally axially from compressor chambers in hollow fan blades (28) and then turned radially outwardly into a combustion chamber (112), where it is then mixed with the fuel and ignited. The combustor has a combustion path extending axially from a forward end of its combustion chamber through a combustion chamber outlet (122) and through a turbine (32) mounted to the fan. Thus, when the core airflow begins to expand in a high-energy gas stream, it has a substantially axial path from the combustion chamber through the turbine.
摘要翻译： 尖端涡轮发动机（40）为周边燃烧器（30）提供通过燃烧器和尖端涡轮机叶片（34）的更有效的燃烧路径。 在燃烧器中，核心气流从中空风扇叶片（28）中的压缩机室大致轴向地接收，然后径向向外转入燃烧室（112），然后与燃料混合并点燃。 燃烧器具有从其燃烧室的前端轴向延伸通过燃烧室出口（122）并通过安装到风扇的涡轮机（32）的燃烧路径。 因此，当核心气流在高能量气流中开始膨胀时，其具有从燃烧室通过涡轮机的基本上轴向的路径。
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公开(公告)号：US20080124211A1
公开(公告)日：2008-05-29
申请号：US11718525
申请日：2004-12-01
IPC分类号： F01D5/14
摘要： A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages (144) at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage (80) toward an axial airflow direction through airflow aspiration at the potentially turbulent locations.
摘要翻译： 风扇 - 涡轮转子组件包括扩散器部分（114），其将来自径向芯气流通道（80）的气流朝向轴向气流方向扩散。 扩散器流动通道在一个位置处与扩散通道（144）连通，当气流从径向核心气流通道（80）通过在潜在湍流位置处的气流抽吸朝向轴向气流方向转动时，气流的分离减小。
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公开(公告)号：US08152469B2
公开(公告)日：2012-04-10
申请号：US11719855
申请日：2004-12-01
摘要： A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.
摘要翻译： 风扇 - 涡轮转子组件（24）包括一个或多个涡轮环转子（32）。 每个涡轮机环形转子都被铸造为一个整体的环形环。 通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏最小化，这增加了发动机效率。 涡轮环转子到扩散器环（114）的组装包括每个涡轮环转子的轴向安装和径向锁定。
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24.发明授权Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine 有权具有整体扩散器部分和尖端涡轮机叶片部分的风扇叶片，用于尖端涡轮发动机公开(公告)号：US07887296B2
公开(公告)日：2011-02-15
申请号：US11719755
申请日：2004-12-01
CPC分类号： F01D5/3007 , F01D1/023 , F01D1/06 , F01D5/022 , F01D5/147 , F01D5/30 , Y02T50/672
摘要： A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.
摘要翻译： 用于尖端涡轮发动机的风扇涡轮机转子组件包括由许多细长开口扇形的外周，所述多个细长开口限定了用于容纳导流部分和中空风扇叶片部分的诱导器接收部分。 每个风扇叶片部分包括从扩散器部分延伸的涡轮部分。
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25.发明授权公开(公告)号：US07874802B2
公开(公告)日：2011-01-25
申请号：US11718522
申请日：2004-12-01
IPC分类号： F01D5/30
CPC分类号： F02C3/073 , F01D5/225 , F01D5/3007 , F02C3/08 , F02K3/068 , F05D2260/30 , Y10T29/49321
摘要： 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.
摘要翻译： 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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26.发明授权公开(公告)号：US07607286B2
公开(公告)日：2009-10-27
申请号：US11719956
申请日：2004-12-01
IPC分类号： F02K3/02
CPC分类号： F02C3/073 , F01D5/022 , F01D5/187 , F02K3/068 , F05D2260/205 , Y02T50/676
摘要： A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through diffuser aspiration passages (146A, 146B) and into the turbine blade passages (150a). The regenerative cooling airflow exits from the turbine blade passage (150a) and transfers received thermal energy into an annular combustor (30). The received thermal energy is recovered at the highest temperature in the cycle.
摘要翻译： 风扇涡轮转子组件（24）包括多个涡轮机叶片（34），每个涡轮机叶片限定一个涡轮机叶片通道，其从扩散器部分（74）排出空气以提供再生冷却。 再生冷却气流通过扩散器抽吸通道（146A，146B）从径向核心气流通道80通过扩散通道144进入涡轮叶片通道150a。 再生冷却气流从涡轮机叶片通道（150a）流出并将接收的热能转移到环形燃烧器（30）中。 接收的热能在循环中的最高温度下回收。
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公开(公告)号：US20080273976A1
公开(公告)日：2008-11-06
申请号：US11709013
申请日：2007-02-21
申请人： Gabriel L. Suciu , Craig A. Nordeen
发明人： Gabriel L. Suciu , Craig A. Nordeen
IPC分类号： F01D7/00
CPC分类号： F01D7/02 , F01D5/148 , F01D5/30 , F04D29/323 , F05D2220/36 , F05D2260/71 , F05D2260/74 , F05D2260/76 , F05D2260/79 , Y02T50/673 , Y10S416/05
摘要： A variable rotor blade mechanism for use in a gas turbine engine comprises a blade rotor, a blade, a harmonic drive system, a stepper motor and a bracket. The blade rotor rotates absolutely about an axial engine centerline during operation of the gas turbine engine. The blade extends radially from the blade rotor and is configured to be adjustable by rotation about a radial axis. The harmonic drive system is mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis. The stepper motor drives the harmonic drive with relative rotational input with respect to the absolute rotation of the blade rotor. The bracket is disposed about the engine centerline and supports the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated.
摘要翻译： 用于燃气涡轮发动机的可变转子叶片机构包括叶片转子，叶片，谐波驱动系统，步进马达和支架。 在燃气涡轮发动机的运行期间，叶片转子绝对围绕轴向发动机中心线旋转。 叶片从叶片转子径向延伸并且构造成通过围绕径向轴线的旋转来调节。 谐波驱动系统安装到叶片转子并连接到叶片以使叶片围绕径向轴线旋转。 步进电机以相对于叶片转子的绝对转动的相对旋转输入驱动谐波驱动器。 支架围绕发动机中心线设置，并且相对于叶片转子的旋转支撑步进马达固定，使得产生对步进马达的相对旋转输入。
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公开(公告)号：US20090133401A1
公开(公告)日：2009-05-28
申请号：US11719225
申请日：2004-12-01
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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公开(公告)号：US20080226453A1
公开(公告)日：2008-09-18
申请号：US11719952
申请日：2004-12-01
申请人： Craig A. Nordeen , Gabriel L. Suciu
发明人： Craig A. Nordeen , Gabriel L. Suciu
IPC分类号： F01D5/22
CPC分类号： F02C3/073 , F01D5/18 , F02K3/068 , F04D25/045 , F04D29/321 , Y02T50/673 , Y02T50/676
摘要： A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section (66), a hollow fan blade section (72) and a diffuser section (74). The hollow fan blade section defines a airflow passage (80). The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes (122). The airflow streams are then further turned by discharge turning vanes (124) before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.
摘要翻译： 用于尖端涡轮发动机的风扇涡轮转子组件包括多个风扇叶片，其包括导流部分（66），中空风扇叶片部分（72）和扩散器部分（74）。 中空风扇叶片部分限定了气流通道（80）。 核心气流通过多个内部转向叶片（122）转动，展开并且分散到扩散器部分的相对端部。 然后在从扩散器排出口排放之前，排气转向叶片（124）进一步转动气流。 随着转动和分离核心气流，风扇叶片轮廓使扩散器部分的质量平衡，使得其中心在中空翼型部分结构之上。
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公开(公告)号：US08807936B2
公开(公告)日：2014-08-19
申请号：US11719952
申请日：2004-12-01
申请人： Craig A. Nordeen , Gabriel L. Suciu
发明人： Craig A. Nordeen , Gabriel L. Suciu
CPC分类号： F02C3/073 , F01D5/18 , F02K3/068 , F04D25/045 , F04D29/321 , Y02T50/673 , Y02T50/676
摘要： A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section, a hollow fan blade section and a diffuser section. The hollow fan blade section defines an airflow passage. The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes. The airflow streams are then further turned by discharge turning vanes before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.
摘要翻译： 用于尖端涡轮发动机的风扇涡轮机转子组件包括多个风扇叶片，其包括导流部分，中空风扇叶片部分和扩散部分。 中空风扇叶片部分限定一个气流通道。 核心气流通过多个内部转向叶片转动，展开并分散到扩散器部分的相对端。 然后在从扩散器排出口排放之前，排气转向叶片进一步转动气流。 随着转动和分离核心气流，风扇叶片轮廓使扩散器部分的质量平衡，使得其中心在中空翼型部分结构之上。
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