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    GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY
    1.
    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：WO2013154639A3

    公开(公告)日：2014-01-03

    申请号：PCT/US2013021831

    申请日：2013-01-17

    Applicant: UNITED TECHNOLOGIES CORP

    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。

    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    4.
    发明专利
    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 未知

    公开(公告)号：SG11201402663XA

    公开(公告)日：2014-09-26

    申请号：SG11201402663X

    申请日：2013-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

    IPC: F01D17/14

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3.

    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    5.
    发明专利
    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 未知

    公开(公告)号：CA2853694A1

    公开(公告)日：2013-07-18

    申请号：CA2853694

    申请日：2013-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

    IPC: F01D17/14

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3.

    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    7.
    发明专利
    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 未知

    公开(公告)号：CA2853694C

    公开(公告)日：2016-03-22

    申请号：CA2853694

    申请日：2013-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

    IPC: F01D17/14 ,  F02C9/20 ,  F02K1/12 ,  F02K3/06 ,  F02K3/075

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3.

    GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY
    8.
    发明公开
    GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY 审中-公开
    具有优良的燃油效率的燃气涡轮发动机

    公开(公告)号：EP2809936A4

    公开(公告)日：2015-09-02

    申请号：EP13775841

    申请日：2013-01-17

    Applicant: UNITED TECHNOLOGIES CORP

    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.

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