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公开(公告)号：US20090142188A1
公开(公告)日：2009-06-04
申请号：US11719296
申请日：2004-12-01
IPC分类号： F01D11/08
CPC分类号： F04D25/045 , F01D11/003 , F01D11/08 , F02C3/073 , F02C7/28 , F02K3/068 , F04D29/083
摘要： A seal assembly (116) mounted within a rotationally fixed static outer support structure (14) for engagement with an annular seal face surface (172) located upon a fan-turbine rotor assembly. The seal assembly provides minimal leakage of core airflow when the airflow is turned and diffused by the diffuser section (74) to increase the engine operating efficiency.
摘要翻译： 安装在旋转固定的静态外部支撑结构（14）内的密封组件（116），用于与位于风扇 - 涡轮转子组件上的环形密封面表面（172）接合。 当气流被扩散器部分（74）转动并扩散时，密封组件提供核心气流的最小泄漏，以提高发动机的运行效率。
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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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15.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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16.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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公开(公告)号：US20090148297A1
公开(公告)日：2009-06-11
申请号：US11719757
申请日：2004-12-01
CPC分类号： F01D5/02 , F01D5/022 , F01D5/3007 , F02C3/073 , F02K3/068 , F04D25/045 , F04D29/54 , F05D2240/55 , F05D2260/30 , F05D2300/603 , Y02T50/672 , Y10T29/49321
摘要： A fan-turbine rotor assembly (24) for a tip turbine engine (10) includes a fan hub (64) with an outer periphery (112) scalloped by a multitude of elongated openings (114) which extend into a fan hub web (115). Each elongated opening defines an inducer receipt section (117) to receive an inducer section (66) and a hollow fan blade section (72). An inducer exhaust from each inducer section is located adjacent a core airflow passage (80) within each fan blade section to provide communication therebetween.
摘要翻译： 一种用于尖端涡轮发动机（10）的风扇涡轮机转子组件（24）包括风扇轮毂（64），其具有由多个细长的开口（114）扇形的外周边（112），所述多个细长的开口延伸到风扇轮毂腹板 ）。 每个细长的开口限定了一个诱导器收容部分（117），用于容纳一个导流部分（66）和一个中空的风扇叶片部分（72）。 来自每个引导部分的诱导物排放物位于每个风扇叶片部分内的核心气流通道80附近，以在它们之间提供连通。
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公开(公告)号：US20090120058A1
公开(公告)日：2009-05-14
申请号：US11720539
申请日：2004-12-01
IPC分类号： F02K3/02
CPC分类号： F01D5/187 , F01D1/023 , F01D5/022 , F01D21/045 , F02C3/045 , F02C3/08 , F02C3/107 , F05D2300/433 , Y02T50/676
摘要： A tip turbine engine assembly includes an integral engine outer case located radially outward from a fan assembly. The integral outer case includes a rear portion and a forward portion with an arcuate portion that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment. Fan inlet guide vanes are integrally formed with the arcuate portion to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally
摘要翻译： 顶端涡轮发动机组件包括从风扇组件径向向外定位的一体式发动机外壳。 一体的外壳包括后部和具有弓形部分的向前部分，其径向向内弯曲以形成隔间。 环形燃烧器容纳并安装在隔室中。 风扇入口导向叶片与弓形部分一体地形成，以形成一体的壳体部分。 后部，前部和风扇入口导向叶片是一体的
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公开(公告)号：US20090056343A1
公开(公告)日：2009-03-05
申请号：US11832107
申请日：2007-08-01
CPC分类号： F02C7/20 , B64D27/18 , B64D27/26 , B64D2027/268 , Y02T50/44 , Y10T29/49826
摘要： An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.
摘要翻译： 发动机安装配置可使发动机推力在后方安装。 发动机安装配置减少了发动机的主干弯曲，中间壳失真和内部机舱内的释放空间。
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20.发明申请Tip Turbine Egine Comprising Turbine Clusters And Radial Attachment Lock Arrangement Therefor 有权涡轮机Egine包括涡轮机组和径向附件锁定装置公开(公告)号：US20080124218A1
公开(公告)日：2008-05-29
申请号：US11718517
申请日：2004-12-01
CPC分类号： F02C3/08 , F01D5/225 , F01D5/3007 , F02C3/073 , F02K3/068 , F05D2260/30 , F05D2260/33 , Y10T29/49245
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. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.
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。 通过将涡轮机叶片组成簇，相邻叶片平台之间的泄漏被最小化，这提高了发动机效率。 将涡轮机叶片组组装到扩散器表面包括每个涡轮叶片组的轴向安装和径向锁定。 这是通过从涡轮机叶片组的弧形底部的下侧突出的附接凸耳来实现的。 扭矩负载表面也集成在弧形底座中。
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