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    Geared turbofan engine with high compressor exit temperature
    1.
    发明授权
    Geared turbofan engine with high compressor exit temperature 有权

    公开(公告)号：US10119466B2

    公开(公告)日：2018-11-06

    申请号：US14950393

    申请日：2015-11-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Karl L. Hasel

    IPC: F02K3/06 ,  F02C3/13 ,  F02C7/36 ,  F02C3/06 ,  F02C3/10

    Abstract: A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

    METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE
    3.
    发明申请
    METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE 审中-公开
    用于设定气体涡轮发动机的风扇驱动齿轮系统的齿轮比的方法

    公开(公告)号：US20160281610A1

    公开(公告)日：2016-09-29

    申请号：US15181102

    申请日：2016-06-13

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Karl L. Hasel

    IPC: F02C7/36 ,  F02C3/107 ,  F02C3/06 ,  F16H1/28

    CPC classification number: F02C7/32 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C3/113 ,  F02C7/00 ,  F02C7/36 ,  F05D2210/12 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/40 ,  F05D2260/40311 ,  F16H1/28 ,  F16H1/36

    Abstract: A gas turbine engine includes an engine centerline longitudinal axis and a fan section including a fan with fan blades and rotatable about the engine centerline longitudinal axis. A low corrected fan tip speed less than about 1400 ft/sec and the low corrected fan tip speed is an actual fan tip speed determined at an ambient temperature divided by [(Tram° R)/(518.7° R)]0.5, where T represents the ambient temperature in degrees Rankine. A bypass ratio greater than about 11 and a speed reduction device having a gear system with a gear ratio and a plurality of bearing systems. A low and high speed spool including a low and high pressure turbine and a first and second shaft, respectively. The first and second shafts are concentric and mounted via at least one of the bearing systems for rotation about the engine centerline longitudinal axis and the first shaft is in communication with the fan through the speed reduction device and the low pressure turbine includes four stages.

    Abstract translation: 燃气涡轮发动机包括发动机中心线纵向轴线和风扇部分，风扇部分包括具有风扇叶片的风扇并可围绕发动机中心线纵向轴线旋转。 小于约1400ft / sec的低校正风扇叶尖速度和低校正风扇叶尖速度是在环境温度除以[（Tram°R）/（518.7°R）] 0.5时确定的实际风扇叶尖速度，其中T 表示环境温度，以度兰为单位。 旁路比大于约11，减速装置具有齿轮系齿轮系和多个轴承系统。 分别包括低压和高压涡轮机以及第一和第二轴的低速和高速线轴。 第一和第二轴是同心的，并且经由至少一个轴承系统安装，用于围绕发动机中心线纵向轴线旋转，并且第一轴通过减速装置与风扇连通，低压涡轮机包括四个阶段。

    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE
    4.
    发明申请
    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE 审中-公开
    具有高压缩机出口温度的齿轮涡轮发动机

    公开(公告)号：US20160076445A1

    公开(公告)日：2016-03-17

    申请号：US14950393

    申请日：2015-11-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Karl L. Hasel

    IPC: F02C3/13 ,  F02C3/06 ,  F02C7/36 ,  F02C3/10

    CPC classification number: F02C3/13 ,  F02C3/06 ,  F02C3/10 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

    Abstract translation: 一种燃气涡轮发动机，包括风扇，其包括可围绕轴线旋转的多个风扇叶片。 压缩机部分包括至少第一压缩机部分和第二压缩机部分，其中第二压缩机部分的部件被构造成在平均出口温度下工作，平均出口温度在大约1000°F至大约1500°F之间。燃烧器处于 与压缩机部分流体连通。 涡轮机部分与燃烧器流体连通。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

    Gas turbine engine shaft bearing configuration
    7.
    发明授权
    Gas turbine engine shaft bearing configuration 有权
    燃气轮机轴承配置

    公开(公告)号：US08863491B2

    公开(公告)日：2014-10-21

    申请号：US14012773

    申请日：2013-08-28

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

    IPC: F02C1/06 ,  F02K3/02

    CPC classification number: F02C7/06 ,  F01D25/162 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/00 ,  F02K3/04 ,  Y02T50/671 ,  Y10T29/4932

    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

    Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向地布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。

    OFF-TAKE POWER RATIO
    8.
    发明申请
    OFF-TAKE POWER RATIO 审中-公开
    取消功率比

    公开(公告)号：US20140090388A1

    公开(公告)日：2014-04-03

    申请号：US13716468

    申请日：2012-12-17

    Applicant: United Technologies Corporation

    Inventor： Karl L. Hasel

    IPC: F02C3/113 ,  F02C7/36 ,  F02C3/04

    CPC classification number: F02C3/113 ,  F02C3/04 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06

    Abstract: An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement of a gas turbine engine; and driving the spool of the gas turbine engine using a second amount of power, wherein a ratio of the first amount of power to the second amount of power is greater than or equal to 0.009.

    Abstract translation: 在燃气涡轮发动机内分配功率的示例性方法包括使用来自阀芯的第一量的功率来驱动取出功率输送组件，所述第一功率量对应于燃气涡轮发动机的取消功率要求; 以及使用第二数量的功率驱动所述燃气涡轮发动机的线轴，其中所述第一功率量与所述第二功率的比率大于或等于0.009。

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