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    COUNTER ROTATING LOW PRESSURE TURBINE WITH SPLITTER GEAR SYSTEM
    1.
    发明申请
    COUNTER ROTATING LOW PRESSURE TURBINE WITH SPLITTER GEAR SYSTEM 审中-公开
    具有分体齿轮系统的逆转低压涡轮机

    公开(公告)号：WO2013172906A2

    公开(公告)日：2013-11-21

    申请号：PCT/US2013/027553

    申请日：2013-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  MCCUNE, Michael E. ,  MAGGE, Shankar S.

    IPC: F02C3/067 ,  F02K3/072

    CPC classification number: F02C3/107 ,  F01D1/26 ,  F02C3/067 ,  F02C7/36 ,  F02K3/072 ,  F05D2250/44 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

    Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴。 外涡轮转子直接驱动轴并且包括外部一组叶片。 内部涡轮转子具有与外部组叶片交替散布的内部一组叶片。 内涡轮转子被构造成围绕与外涡轮转子的旋转轴线相反的方向旋转。 分动齿轮系统将内涡轮转子与轴连接，并且构造成以比外套叶片更快的速度旋转内组叶片。

    TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES
    2.
    发明申请
    TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES 审中-公开
    两台气体发生器创造气体涡轮发动机系列

    公开(公告)号：WO2014098962A1

    公开(公告)日：2014-06-26

    申请号：PCT/US2013/043039

    申请日：2013-05-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F02C6/00 ,  F02C6/02 ,  F02C9/00 ,  F02C7/00

    CPC classification number: F02C6/02 ,  F02C3/10 ,  F02C7/06 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/324 ,  F05D2220/326 ,  F05D2250/31 ,  F05D2260/4031

    Abstract: A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.

    Abstract translation: 配置多个燃气涡轮发动机的方法包括以下步骤：用多个推进器中的相应的发动机配置每个发动机。 每个推进器包括推进涡轮机和风扇和螺旋桨之一。 每个发动机配置有多个基本上相互相似的气体发生器中的相应的发动机，相应的推进涡轮机由气体发生器下游的燃烧产物驱动。

    LOW SPOOL STARTER SYSTEM FOR GAS TURBINE ENGINE
    7.
    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：WO2014134256A1

    公开(公告)日：2014-09-04

    申请号：PCT/US2014/018877

    申请日：2014-02-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SHERIDAN, William G. ,  SUCIU, Gabriel L. ,  MERRY, Brian D.

    IPC: F02C7/26 ,  F02C7/32

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

    Abstract: A gas turbine engine 10 comprises a first compressor 14, a second compressor 18, a starter generator 12 and a clutch 16. The starter generator 12 is coupled to the first compressor 14. The clutch 16 selectively couples the second compressor 18 and the first compressor 14. The clutch 16 is disposed between a first shaft 78B and a second shaft 22 to engage the first shaft 78B with the second shaft 22 at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft 78B relative to the second shaft 22 when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine 10 comprises engaging a low pressure compressor 14 with a high pressure compressor 18 utilizing a clutch 16, rotating the low pressure compressor 14 and the high pressure compressor 18 utilizing a starter generator 12 coupled to the low pressure compressor 14, igniting the gas turbine engine 10, and disengaging the clutch 16 at an operational speed of the gas turbine engine 10.

    Abstract translation: 燃气涡轮发动机10包括第一压缩机14，第二压缩机18，起动发电机12和离合器16.起动发电机12联接到第一压缩机14.离合器16选择性地将第二压缩机18和第一压缩机 离合器16设置在第一轴78B和第二轴22之间，以使第一轴78B与静止的第二轴22接合。 飞行重量系统与离合器机构接合，以允许当超过阈值速度的旋转运动时第一轴78B相对于第二轴22的续流。 用于启动燃气涡轮发动机10的方法包括利用离合器16将低压压缩机14与高压压缩机18接合，利用联接到低压压缩机的起动器发电机12来旋转低压压缩机14和高压压缩机18 如图14所示，点燃燃气涡轮发动机10，并以燃气轮机发动机10的运转速度离合离合器16。

    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES
    8.
    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：WO2014018142A3

    公开(公告)日：2014-01-30

    申请号：PCT/US2013/037675

    申请日：2013-04-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard ,  MERRY, Brian D. ,  ACKERMANN, William K.

    IPC: F01D25/16 ,  F02C7/06

    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，使得由低压涡轮机的出口面积所限定的量乘以低压涡轮机转速的平方与相同的参数 因为高压涡轮机的比率在大约0.5和大约1.5之间。 高压涡轮机由定位在第一轴连接到携带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 COMPRESSOR ARRANGEMENT
    10.
    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。

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