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    TURBOFAN ENGINE FRONT SECTION
    6.
    发明申请
    TURBOFAN ENGINE FRONT SECTION 审中-公开
    涡轮发动机前部分

    公开(公告)号：WO2014182546A2

    公开(公告)日：2014-11-13

    申请号：PCT/US2014036475

    申请日：2014-05-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  SHERIDAN WILLIAM G

    CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2260/40311

    Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between about 219 and 328.

    Abstract translation: 涡扇发动机包括用于围绕轴驱动风扇的齿轮架构。 齿轮架构包括围绕轴线旋转的太阳齿轮，由太阳齿轮驱动的多个行星齿轮和围绕多个行星齿轮的环形齿轮。 载体支撑多个行星齿轮。 齿轮架构包括功率传递参数（PTP），定义为通过齿轮传动结构传递的功率，除以齿轮容积乘以齿轮减速比，并在219和328之间。

    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES
    7.
    发明申请
    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开
    具有高速低压涡轮部分和轴承支撑特征的燃气涡轮发动机

    公开(公告)号：WO2014018142A2

    公开(公告)日：2014-01-30

    申请号：PCT/US2013037675

    申请日：2013-04-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  MERRY BRIAN D ,  ACKERMANN WILLIAM K

    CPC classification number: F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02K3/06

    Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

    Abstract translation: 燃气涡轮发动机包括超高速低压涡轮机，使得与低压涡轮机的相同参数相比，由低压涡轮机的出口面积乘以低压涡轮机转速的平方所确定的量处于 比率在约0.5和约1.5之间。 高压涡轮机由位于第一轴连接到承载与第二涡轮机部分相关联的涡轮机转子的轮毂的点处的轴承支撑。

    GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE
    8.
    发明申请
    GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE 审中-公开
    燃气涡轮发动机与风扇变化区域喷嘴

    公开(公告)号：WO2013141934A2

    公开(公告)日：2013-09-26

    申请号：PCT/US2012071946

    申请日：2012-12-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLENBERG GREGORY A ,  ZAMORA SEAN P ,  SCHWARZ FREDERICK M

    IPC: F01D17/00 ,  F01D15/12

    CPC classification number: F02K1/09 ,  F02K3/06 ,  F02K3/075

    Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

    Abstract translation: 用于高旁通燃气涡轮发动机的机舱组件包括可相对于风扇机舱移动的风扇可变区域喷嘴，以改变风扇喷嘴出口区域并调节发动机运行期间风扇旁路气流的压力比。

    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE
    9.
    发明申请
    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE 审中-公开
    超高压比汽油涡轮发动机

    公开(公告)号：WO2015119698A3

    公开(公告)日：2015-11-05

    申请号：PCT/US2014066094

    申请日：2014-11-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L

    IPC: F02C3/107

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a first turbine rotor positioned upstream of a second intermediate turbine rotor and a third turbine rotor positioned downstream of the first and second turbine rotors. A fan rotor and three compressor rotors, with an upstream one of the compressor rotors are connected to rotate on a shaft with a fan drive turbine and a reduced speed fan rotor through a gear reduction. A second intermediate compressor rotor for being driven by the second intermediate turbine rotor, and a third compressor rotor downstream of the first and second compressor rotors and for being driven by the first turbine rotor.

    Abstract translation: 燃气涡轮发动机包括位于第二中间涡轮转子上游的第一涡轮转子和位于第一涡轮转子和第二涡轮转子下游的第三涡轮转子。 风扇转子和三个压缩机转子与上游的一个压缩机转子连接以通过齿轮减速器在具有风扇驱动涡轮机和减速风扇转子的轴上旋转。 用于由第二中间涡轮转子驱动的第二中间压缩机转子以及位于第一压缩机转子和第二压缩机转子下游并且由第一涡轮转子驱动的第三压缩机转子。

    GEARED TURBOFAN WITH THREE CO-ROTATING TURBINES
    10.
    发明申请
    GEARED TURBOFAN WITH THREE CO-ROTATING TURBINES 审中-公开
    具有三个旋转涡轮的齿轮涡轮机

    公开(公告)号：WO2014007896A3

    公开(公告)日：2014-04-10

    申请号：PCT/US2013034537

    申请日：2013-03-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

    IPC: F02C3/04

    CPC classification number: F02K3/075 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2260/40311

    Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan rotor through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine rotate in the same direction.

    Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮通过齿轮减速器驱动风扇转子。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速卷轴，中速卷轴和风扇驱动涡轮机沿相同方向旋转。

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