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    NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT WITH LINKAGE BETWEEN ADJACENT ROTORS
    112.
    发明公开
    NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT WITH LINKAGE BETWEEN ADJACENT ROTORS 审中-公开
    联系LOOSE密封装置与BETWEEN近域ROTORS连接的旋转设备

    公开(公告)号：EP3115659A1

    公开(公告)日：2017-01-11

    申请号：EP16178693.4

    申请日：2016-07-08

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M. ,  ACKERMANN, William K.

    IPC分类号： F16J15/3284 ,  F01D11/00 ,  F01D11/04 ,  F16J15/44

    CPC分类号： F01D11/08 ,  B64D27/10 ,  F01D11/001 ,  F01D11/003 ,  F01D11/02 ,  F04D29/324 ,  F04D29/545 ,  F05D2220/32 ,  F05D2240/55 ,  F16J15/3284 ,  F16J15/44 ,  F16J15/442

    摘要： An assembly is provided for rotational equipment such as a gas turbine engine 10 for an aircraft propulsion system. This assembly includes a stator 52, a rotor 54 and a seal assembly 108. The rotor 54 extends axially along a centerline 12. The rotor 54 includes a linkage 92A, a first rotor disk 90A, and a second rotor disk 90B. The linkage 92A extends axially from the first rotor disk 90A to the second rotor disk 90B. The linkage 92A is removably attached to the second rotor disk 90B. The seal assembly 108 is configured for sealing a gap radially between the stator 52 and the linkage 92A. The seal assembly 108 includes a hydrostatic non-contact seal.

    摘要翻译： 提供了一种组件，用于旋转的设备：诸如燃气涡轮发动机10的飞机推进系统上该组件包括一个定子52，一个转子54和一个密封组件108。转子54沿中心线12的转子54包括沿轴向延伸 连杆92A，第一转子盘90A，和第二转子盘90B。 连杆92A从第一转子盘90A到第二转子盘90B轴向延伸。 连杆92A可拆卸地连接到第二转子盘90B。 密封组件108被配置为径向密封定子52和连杆92A之间的间隙。 密封组件108包括一个液压静力非接触密封件。

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    113.
    发明公开
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    TURBINENABSCHNITT EINES HOCHBYPASS-TURBOFANS

    公开(公告)号：EP3115590A1

    公开(公告)日：2017-01-11

    申请号：EP16178679.3

    申请日：2016-07-08

    申请人： United Technologies Corporation

    发明人： ADAMS, Paul R. ,  MAGGE, Shankar S. ,  STAUBACH, Joseph B. ,  LORD, Wesley K. ,  SCHWARZ, Frederick M. ,  SUCIU, Gabriel L.

    IPC分类号： F02K3/06 ,  F02C3/107 ,  F02C7/36

    CPC分类号： F02K3/06 ,  F02C3/107 ,  F05D2250/30 ,  F05D2260/40311

    摘要： A turbofan engine (20) comprises a fan (42) having fan blades (70). A compressor is in communication with the fan section. The fan (42) is configured to communicate a portion of air into a bypass path defining a bypass area outwardly of the compressor and a portion into the compressor. A bypass ratio is greater than 6.0. A combustor (48) is in fluid communication with the compressor. A turbine is in communication with the combustor (48). The turbine has a first turbine section (27) that includes two or more stages (200, 202, 204) and a second turbine section (26) that includes at least two stages. A ratio of airfoils in the first turbine section (27) to the bypass ratio is less than 170. The first turbine section (27) includes a maximum gas path radius. A ratio of the maximum gas path radius to a maximum radius of the fan blades (70) is less than 0.50. A speed reduction mechanism (46) is coupled to the fan (42) and rotatable by the turbine.

    摘要翻译： 涡扇发动机（20）包括具有风扇叶片（70）的风扇（42）。 压缩机与风扇部分连通。 风扇（42）被构造成将空气的一部分连通到限定压缩机外侧的旁路区域的旁通路径和压缩机的一部分。 旁路比大于6.0。 燃烧器（48）与压缩机流体连通。 涡轮机与燃烧器（48）连通。 涡轮机具有包括两个或多个级（200,202,204）的第一涡轮部分（27）和包括至少两个级的第二涡轮机部分（26）。 第一涡轮部分（27）中的翼型件与旁路比的比率小于170.第一涡轮部分（27）包括最大气体路径半径。 风扇叶片（70）的最大气路半径与最大半径的比小于0.50。 减速机构（46）联接到风扇（42）并由涡轮机旋转。

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    114.
    发明公开
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    TURBINENABSCHNITT EINES TURBOFAN MIT HOHEMNEBENSTROMVERHÄLTNIS

    公开(公告)号：EP3115576A1

    公开(公告)日：2017-01-11

    申请号：EP16178691.8

    申请日：2016-07-08

    申请人： United Technologies Corporation

    发明人： ADAMS, Paul R. ,  MAGGE, Shankar S. ,  STAUBACH, Joseph B. ,  LORD, Wesley K. ,  SCHWARZ, Frederick M. ,  SUCIU, Gabriel L.

    IPC分类号： F02C7/36 ,  F01D15/12 ,  F02K3/04 ,  F02K3/068

    CPC分类号： F02C7/36 ,  F02K3/068 ,  F05D2220/36 ,  F05D2260/40311

    摘要： A turbofan engine (20) includes an engine case (22), a gaspath through the engine case (22), a fan (42) having an array of fan blades, a compressor in fluid communication with the fan (42), a combustor (48) in fluid communication with the compressor, and a turbine in fluid communication with the combustor (48). The turbine has a fan drive turbine section (27) having 3 to 6 blade stages (200, 202, 204) and a second turbine section (26). A speed reduction mechanism (46) couples the fan drive turbine (27) section to the fan (42). A ratio of maximum gaspath radius along the fan drive turbine section (27) to maximum radius of the fan blades is less than 0.55. A bypass area ratio is greater than 6.0. A ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than 170.

    摘要翻译： 涡轮风扇发动机（20）包括发动机壳体（22），通过发动机机壳（22）的气路，具有风扇叶片阵列的风扇（42），与风扇（42）流体连通的压缩机，燃烧器 （48）与所述压缩机流体连通，以及与所述燃烧器（48）流体连通的涡轮机。 涡轮机具有风扇驱动涡轮机部分（27），其具有3至6个叶片级（200,202,204）和第二涡轮部分（26）。 减速机构（46）将风扇驱动涡轮机（27）部分连接到风扇（42）。 风扇驱动涡轮部分（27）的最大气路径半径与风扇叶片的最大半径之比小于0.55。 旁路面积比大于6.0。 风扇驱动涡轮机翼型计数与旁路面积比的比值小于170。

    GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT
    116.
    发明公开
    GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT 审中-公开
    燃气涡轮发动机的长途飞机

    公开(公告)号：EP3084195A2

    公开(公告)日：2016-10-26

    申请号：EP14880953.6

    申请日：2014-11-07

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M. ,  SUCIU, Gabriel L.

    IPC分类号： F02K3/06 ,  F02K3/075 ,  F02C9/16

    CPC分类号： F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  F05D2260/40311

    摘要： A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.

    GEARED TURBOFAN WITH THREE TURBINE SECTIONS
    117.
    发明公开
    GEARED TURBOFAN WITH THREE TURBINE SECTIONS 审中-公开
    带有三个涡轮分段的齿轮涡轮增压器

    公开(公告)号：EP3084173A2

    公开(公告)日：2016-10-26

    申请号：EP14880333.1

    申请日：2014-11-07

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M. ,  STAUBACH, Joseph Brent

    IPC分类号： F02C3/073 ,  F02K3/06

    CPC分类号： F02K3/06 ,  F02C7/36 ,  F05D2260/40311

    摘要： A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flow into a core engine where it reaches an upstream compressor rotor. The upstream compressor rotor is configured to be driven through a second shaft by an intermediate turbine rotor. A downstream compressor rotor is configured to be driven by an upstream turbine rotor through a third shaft. An overall pressure ratio across the upstream and downstream compressor rotors is greater than or equal to about 35.0 and less than or equal to about 75.0.

    摘要翻译： 燃气涡轮发动机包括风扇转子，该风扇转子构造成通过第一轴和齿轮减速器由风扇驱动涡轮驱动。 风扇转子被配置为将空气作为旁路空气输送到旁路管道中并且将核心空气流输送到核心发动机中，在那里它到达上游压缩机转子。 上游压缩机转子构造成由中间涡轮机转子驱动通过第二轴。 下游压缩机转子构造成通过第三轴由上游涡轮机转子驱动。 跨越上游和下游压缩机转子的整体压力比大于或等于约35.0且小于或等于约75.0。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    118.
    发明公开
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
    齿轮涡轮增压燃气轮机发动机结构

    公开(公告)号：EP3070315A1

    公开(公告)日：2016-09-21

    申请号：EP16161464.9

    申请日：2016-03-21

    申请人： United Technologies Corporation

    发明人： HOUSTON, David P. ,  KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    IPC分类号： F02K3/06 ,  F02C3/067 ,  F02C7/36

    CPC分类号： F02K3/06 ,  F02C3/067 ,  F02C3/107 ,  F05D2250/00 ,  F05D2260/40311 ,  Y02T50/671

    摘要： A gas turbine engine (20) includes a fan (42) rotatable about an axis (A), a compressor section (24), a combustor (56) in fluid communication with the compressor section (24), and a turbine section (28) in fluid communication with the combustor (56). The turbine section (28) includes a fan drive turbine (46), a second turbine that drives a compressor rotor and one other turbine driving another compressor rotor of the compressor section (24). The second turbine (54) is disposed forward of the fan drive turbine (46). The fan drive turbine (46) includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system (48) is driven by the fan drive turbine (46) for rotating the fan (42) about the axis (A).

    摘要翻译： 燃气涡轮发动机（20）包括可绕轴线（A）旋转的风扇（42），压缩机部分（24），与压缩机部分（24）流体连通的燃烧器（56），以及涡轮部分 ）与燃烧器（56）流体连通。 涡轮机部分（28）包括风扇驱动涡轮机（46），驱动压缩机转子的第二涡轮机和驱动压缩机部分（24）的另一压缩机转子的另一涡轮机。 第二涡轮机（54）配置在风扇驱动涡轮机（46）的前方。 风扇驱动涡轮机（46）包括至少三个转子和至少一个具有孔径半径（R）和活动轮缘半径（r）的转子，并且r / R的比率在约2.00和约2.30之间。 变速系统（48）由风扇驱动涡轮（46）驱动，以使风扇（42）绕轴线（A）旋转。

    GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO
    119.
    发明公开
    GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO 审中-公开
    GETRIEBETURBOLÜFTERANORDNUNGMIT GETERILTER KERNLEISTUNG

    公开(公告)号：EP3063385A2

    公开(公告)日：2016-09-07

    申请号：EP14880285.3

    申请日：2014-10-29

    申请人： United Technologies Corporation

    发明人： KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    IPC分类号： F02C1/06

    CPC分类号： F02C3/107 ,  F01D5/187 ,  F05D2300/606 ,  Y02T50/672 ,  Y02T50/676

    摘要： A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.

    摘要翻译： 燃气涡轮发动机包括风扇部分和压缩机部分。 压缩机部分包括第一压缩机部分和第二压缩机部分。 涡轮部分包括至少一个涡轮机并且驱动第二压缩机部分和驱动至少一个齿轮装置以驱动风扇部分的风扇驱动涡轮机。 功率比由第一压缩机部分和第二压缩机部分的组合提供，功率比由第一功率输入提供给第一压缩机部分，第二功率输入到第二压缩机部分，功率比是 等于或大于约1.0且小于或等于约1.4。

    GEARED TURBOFAN ENGINE WITH TARGETED MODULAR EFFICIENCY
    120.
    发明公开
    GEARED TURBOFAN ENGINE WITH TARGETED MODULAR EFFICIENCY 审中-公开
    TURBOGEBLÄSEMOTORMIT GEZIELTER MODULARER WIRKUNG

    公开(公告)号：EP3058202A2

    公开(公告)日：2016-08-24

    申请号：EP14870182.4

    申请日：2014-09-24

    申请人： United Technologies Corporation

    发明人： SCHWARZ, Frederick M.

    IPC分类号： F02C7/36

    CPC分类号： F02C3/107 ,  F01D5/142 ,  F02K3/06 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/671 ,  Y02T50/673

    摘要： A turbofan engine includes a fan section including a fan blade having a leading edge and hub to tip ratio of less than about 0.34 and greater than about 0.020 measured at the leading edge and a speed change mechanism with gear ratio greater than about 2.6 to 1. A first compression section includes a last blade trailing edge radial tip length that is greater than about 67% of the radial tip length of a leading edge of a first stage of the first compression section. A second compression section includes a last blade trailing edge radial tip length that is greater than about 57% of a radial tip length of a leading edge of a first stage of the first compression section.

    摘要翻译： 涡轮风扇发动机包括风扇部分，风扇部分包括风扇叶片，风扇叶片具有在前缘处测量的小于约0.34且大于约0.020的前缘和毂与尖端比率以及齿轮比大于约2.6至1的变速机构。 第一压缩部分包括最大叶片后缘径向尖端长度，其大于第一压缩部分的第一级的前缘的径向尖端长度的约67％。 第二压缩部分包括最大刀片后缘径向尖端长度，其大于第一压缩部分的第一级的前缘的径向尖端长度的约57％。