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    GEARED TURBOFAN ENGINE GEARBOX ARRANGEMENT
    37.
    发明申请
    GEARED TURBOFAN ENGINE GEARBOX ARRANGEMENT 审中-公开
    齿轮式涡轮发动机齿轮箱装置

    公开(公告)号：US20160153356A1

    公开(公告)日：2016-06-02

    申请号：US15013125

    申请日：2016-02-02

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

    IPC: F02C3/107 ,  F02C3/10 ,  F04D29/32 ,  F01D17/10 ,  F01D9/06 ,  F01D5/02 ,  F02C3/06 ,  F02C7/36

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括具有多个风扇叶片的风扇部分。 多个风扇叶片在第一流路的第一内侧边界处具有顶尖半径Rt和内侧前缘半径Rh。 核心发动机包括构造成驱动第一压缩机的第一涡轮机和配置成驱动风扇部分的风扇驱动涡轮机。 还公开了一种设计燃气涡轮发动机的方法。

    Turbofan Engine Bearing and Gearbox Arrangement
    39.
    发明申请
    Turbofan Engine Bearing and Gearbox Arrangement 审中-公开
    涡轮发动机轴承和齿轮箱布置

    公开(公告)号：US20160025003A1

    公开(公告)日：2016-01-28

    申请号：US14776080

    申请日：2014-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

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

    CPC classification number: F02C3/107 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F04D25/028 ,  F04D29/059 ,  F04D29/321 ,  F05D2260/40311

    Abstract: A turbofan engine (300; 600; 700) comprising a fan shaft (120) configured to rotate about an axis (500) of the engine. A fan drive gear system (60) is configured to drive the fan shaft. The fan drive gear system has a centerplane (540). A first spool comprises a high pressure turbine (326) and a high pressure compressor (324). A second spool comprises an intermediate pressure turbine (328), a lower pressure compressor, and a shaft (334) coupling the intermediate pressure turbine to the lower pressure compressor. A third spool comprises a lower pressure turbine (330) coupled to the fan drive gear system to drive the fan. The engine has a plurality of main bearings. The turbofan engine has a single stage fan. Of the main bearings, at least one is a shaft-engaging bearing engaging a driving shaft (336) coupled to the fan drive gear system. A closest (340; 640) of the shaft-engaging bearings engaging the driving shaft behind the fan drive gear system has a centerplane (550) and a characteristic radius (RB). The half angle (θ) of a virtual cone (530) intersecting the core flowpath inboard boundary at the gear system centerplane (540) and said closest of the shaft-engaging bearings at the characteristic radius (RB) is greater than about 32°. A hub-to-tip ratio (HR:FR) of the fan is less than about 0.38.

    Abstract translation: 涡轮风扇发动机（300; 600; 700）包括构造成围绕发动机的轴线（500）旋转的风扇轴（120）。 风扇驱动齿轮系统（60）构造成驱动风扇轴。 风扇驱动齿轮系统具有中心面（540）。 第一阀芯包括高压涡轮机（326）和高压压缩机（324）。 第二卷轴包括中压涡轮机（328），低压压缩机以及将中压涡轮机与低压压缩机联接的轴（334）。 第三卷轴包括联接到风扇驱动齿轮系统以驱动风扇的低压涡轮机（330）。 发动机具有多个主轴承。 涡扇发动机具有单级风扇。 在主轴承中，至少一个是与联接到风扇驱动齿轮系统的驱动轴（336）接合的轴接合轴承。 与风扇驱动齿轮系统后面的驱动轴接合的轴接合轴承的最接近（340; 640）具有中心面（550）和特征半径（RB）。 与齿轮系中心平面（540）处的内侧边界处的核心流路相交的虚拟锥体（530）和特征半径（RB）处的所述最接近的轴接合轴承的半角（＆amp; tt）大于约32° 。 风扇的轮毂比（HR：FR）小于约0.38。

    LOW SPOOL STARTER SYSTEM FOR GAS TURBINE ENGINE
    40.
    发明申请
    LOW SPOOL STARTER SYSTEM FOR GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的低气压起动器系统

    公开(公告)号：US20150377142A1

    公开(公告)日：2015-12-31

    申请号：US14767477

    申请日：2014-02-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William G. Sheridan ,  Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02C7/275 ,  F02C3/107

    CPC classification number: F02C7/275 ,  F01D19/00 ,  F02C3/107 ,  F02C7/36 ,  F05D2260/40 ,  F05D2260/403 ,  F05D2260/85

    Abstract: A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine.

    Abstract translation: 燃气涡轮发动机包括第一压缩机，第二压缩机，起动发电机和离合器。 起动发电机联接到第一压缩机。 离合器选择性地联接第二压缩机和第一压缩机。 离合器设置在第一轴和第二轴之间，以使第一轴与静止的第二轴接合。 飞行重量系统与离合器机构接合以允许当经受超过阈值速度的旋转运动时第一轴相对于第二轴的续流。 一种用于启动燃气涡轮发动机的方法包括使用离合器将低压压缩机与高压压缩机接合，利用联接到低压压缩机的启动发电机旋转低压压缩机和高压压缩机，点燃燃气涡轮发动机， 以及在所述燃气涡轮发动机的操作速度下离合所述离合器。

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