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公开(公告)号：US07966807B2
公开(公告)日：2011-06-28
申请号：US11654472
申请日：2007-01-17
申请人： James W. Norris , James D. Hill , Craig A. Nordeen
发明人： James W. Norris , James D. Hill , Craig A. Nordeen
CPC分类号： F02C6/08 , F01D9/065 , F01D25/12 , F02C7/16 , F02K3/06 , F05D2240/55 , F05D2260/208 , F05D2260/221 , F05D2260/232
摘要： A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly, wherein the vaporization section is located at least partially within the non-rotating component, and wherein the condenser section is located outside the non-rotating component and away from the engine flowpath.
摘要翻译： 用于燃气涡轮发动机的冷却系统包括延伸到发动机流动路径中的非旋转部件，蒸汽冷却组件，其被配置为通过循环蒸发和冷凝密封在蒸气中的工作介质将热能从蒸发部分输送到冷凝器部分 冷却组件，其中所述蒸发部分至少部分地位于所述非旋转部件内，并且其中所述冷凝器部分位于所述非旋转部件的外部并且远离所述发动机流动路径。
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公开(公告)号：US20100263388A1
公开(公告)日：2010-10-21
申请号：US11654472
申请日：2007-01-17
申请人： James W. Norris , James D. Hill , Craig A. Nordeen
发明人： James W. Norris , James D. Hill , Craig A. Nordeen
IPC分类号： F02C7/18
CPC分类号： F02C6/08 , F01D9/065 , F01D25/12 , F02C7/16 , F02K3/06 , F05D2240/55 , F05D2260/208 , F05D2260/221 , F05D2260/232
摘要： A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly, wherein the vaporization section is located at least partially within the non-rotating component, and wherein the condenser section is located outside the non-rotating component and away from the engine flowpath.
摘要翻译： 用于燃气涡轮发动机的冷却系统包括延伸到发动机流动路径中的非旋转部件，蒸汽冷却组件，其被配置为通过循环蒸发和冷凝密封在蒸气中的工作介质将热能从蒸发部分输送到冷凝器部分 冷却组件，其中所述蒸发部分至少部分地位于所述非旋转部件内，并且其中所述冷凝器部分位于所述非旋转部件的外部并且远离所述发动机流动路径。
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公开(公告)号：US08468795B2
公开(公告)日：2013-06-25
申请号：US11718525
申请日：2004-12-01
IPC分类号： F02K3/02
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：US08104257B2
公开(公告)日：2012-01-31
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： F02C3/045
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：US08033092B2
公开(公告)日：2011-10-11
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 formed in a casting process.
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在铸造过程中一体地形成。
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公开(公告)号：US07927075B2
公开(公告)日：2011-04-19
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：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：US09541092B2
公开(公告)日：2017-01-10
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：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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