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    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE
    2.
    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：WO2014055114A1

    公开(公告)日：2014-04-10

    申请号：PCT/US2013/030407

    申请日：2013-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  HASEL, Karl L.

    IPC: F02K3/04 ,  F02K3/00 ,  F01D9/02

    CPC classification number: F02C3/13 ,  F01D5/34 ,  F02K3/06 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000 °F and about 1500 °F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that 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: 燃气涡轮发动机包括具有可围绕轴线旋转的多个风扇叶片的风扇和至少包括第一和第二压缩机部分的压缩机部分。 压缩机部分的平均出口温度在约1000°F至约1500°F之间。 发动机还包括与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

    RELATIONSHIP BETWEEN FAN AND PRIMARY EXHAUST STREAM VELOCITIES IN A GEARED GAS TURBINE ENGINE
    3.
    发明申请
    RELATIONSHIP BETWEEN FAN AND PRIMARY EXHAUST STREAM VELOCITIES IN A GEARED GAS TURBINE ENGINE 审中-公开
    风机涡轮发动机风扇与主流排风流之间的关系

    公开(公告)号：WO2014113038A1

    公开(公告)日：2014-07-24

    申请号：PCT/US2013/022402

    申请日：2013-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HASEL, Karl L.

    IPC: F02K3/02

    CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2260/4031

    Abstract: An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is approximately in a first range of 2.4 to 4.2. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a second range of 0.75 to 0.90.

    Abstract translation: 一个示例性的燃气涡轮发动机包括可将风扇驱动轴可旋转地联接到发动机风扇的齿轮架构，该齿轮架构具有大约在2.4至4.2的第一范围内的减速比。 燃气涡轮发动机构造成使得由风扇排气速度与一次排气速度的比率所限定的排气速度比大约在0.75至0.90的第二范围内。

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    4.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 审中-公开
    燃气涡轮发动机压缩机装置

    公开(公告)号：WO2013101805A1

    公开(公告)日：2013-07-04

    申请号：PCT/US2012/071614

    申请日：2012-12-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HASEL, Karl L. ,  STAUBACH, Joseph B. ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  DYE, Christohper M.

    IPC: F01D1/04

    CPC classification number: F02C3/107 ,  F02K3/06

    Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

    Abstract translation: 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而高压压缩机部分的压力比为约7至约15。

    GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY
    7.
    发明申请
    GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY 审中-公开
    具有改进燃油效率的燃气涡轮发动机

    公开(公告)号：WO2013154639A2

    公开(公告)日：2013-10-17

    申请号：PCT/US2013/021831

    申请日：2013-01-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HASEL, Karl L. ,  SMITH, Peter G. ,  OCHS, Stuart S.

    IPC: F02K3/02

    CPC classification number: F01D17/162 ,  F04D29/563 ,  F05D2220/36 ,  F05D2240/121

    Abstract: A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

    Abstract translation: 涡轮风扇发动机包括由低压涡轮机通过齿轮减速器驱动的风扇。 齿轮减速器具有大于或等于约2.4的齿轮比。 低压涡轮机具有大于或等于约5的膨胀比。风扇具有大于或等于约8的旁通比。在其它特征中，涡轮风扇发动机包括可变几何风扇出口导叶（FEGV）系统，其具有 周向间隔开的径向延伸的风扇出口导叶的多个。 风扇出口导向叶片在标称位置和旋转位置之间的旋转选择性地改变风扇旁路流动路径以允许在各种飞行条件下的有效操作。

    HIGH THRUST GEARED GAS TURBINE ENGINE
    8.
    发明申请
    HIGH THRUST GEARED GAS TURBINE ENGINE 审中-公开

    公开(公告)号：WO2015050619A3

    公开(公告)日：2015-04-09

    申请号：PCT/US2014/046781

    申请日：2014-07-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  HASEL, Karl L. ,  MERRY, Brian D.

    IPC: F02C7/00 ,  F02C7/32

    Abstract: A ratio of an outer diameter of a fan hub at a leading edge of the blades to an outer tip diameter of the blades at the leading edge is greater than or equal to about 0.24 and less than or equal to about 0.38. The fan tip diameter is greater than or equal to about 84 inches (213.36 centimeters) and a fan tip speed is less than or equal to about 1050 ft / second (320.04 meters / second). A bypass ratio, a gear ratio and an AN2 value are also claimed. The fan drive turbine has between three and six stages.

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    9.
    发明申请
    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 审中-公开
    气体涡轮发动机轴承轴承配置

    公开(公告)号：WO2015047489A1

    公开(公告)日：2015-04-02

    申请号：PCT/US2014/043195

    申请日：2014-06-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L. ,  HASEL, Karl L.

    IPC: F02C1/06 ,  F02K3/02

    CPC classification number: F02C7/36 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F05D2260/40311

    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。

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