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    JET NOISE SUPPRESSOR FOR GAS TURBINE ENGINE
    1.
    发明专利
    JET NOISE SUPPRESSOR FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JP2000145475A

    公开(公告)日：2000-05-26

    申请号：JP24721499

    申请日：1999-09-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  LORD WESLEY K ,  KOHLENBERG GREGORY A

    IPC: F02C7/045 ,  F02K1/38 ,  F02K1/46 ,  F02K1/48 ,  F02K3/02

    Abstract: PROBLEM TO BE SOLVED: To provide a jet noise suppression system having an enhanced suppression effect for an engine in high power level operation. SOLUTION: This jet noise suppressor for a gas turbine engine has no adverse effect on thrust and performance of an engine. The jet noise suppressor includes a nozzle and is provided with a disposition of tabs 40 arranged at a downstream end of the nozzle. The tabs 40 possess a squarish offset with respect to its length and an engine stream, and cause mixing at the boundary of the engine stream and ambient air. A tab shape which is a trapezoid having tapered side faces 55 reduces any adverse effect on engine performance.

    GEARED TURBINE ENGINE WITH A D-DUCT AND A THRUST REVERSER
    2.
    发明申请
    GEARED TURBINE ENGINE WITH A D-DUCT AND A THRUST REVERSER 审中-公开
    带有D型导管和推力反向器的齿轮式发动机

    公开(公告)号：WO2014116308A3

    公开(公告)日：2014-10-02

    申请号：PCT/US2013064351

    申请日：2013-10-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOHLENBERG GREGORY A

    IPC: F02K3/06 ,  F02K3/075

    CPC classification number: F02C7/36 ,  F01D15/12 ,  F02C3/04 ,  F02K1/06 ,  F02K1/09 ,  F02K1/68 ,  F02K1/72

    Abstract: A geared turbine engine includes a first rotor, a second rotor, a gear train and an engine casing. The rotors and the gear train are arranged along an axial centerline. The gear train connects the first rotor to the second rotor. The casing extends circumferentially around the centerline and houses the first rotor, the second rotor and/or the gear train. The casing includes a casing door. The casing door includes a duct and a thrust reverser. The duct extends axially along and at least partially around the centerline.

    Abstract translation: 齿轮涡轮发动机包括第一转子，第二转子，齿轮系和发动机壳体。 转子和齿轮系沿轴向中心线布置。 齿轮系将第一转子连接到第二转子。 壳体围绕中心线圆周地延伸并容纳第一转子，第二转子和/或齿轮系。 外壳包括外壳门。 套管门包括一个管道和一个推力反向器。 该管道沿着中心线轴向延伸并且至少部分地围绕中心线延伸。

    GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY
    3.
    发明申请
    GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY 审中-公开
    齿轮涡喷头初级和次级喷嘴集成几何

    公开(公告)号：WO2014105237A3

    公开(公告)日：2014-08-21

    申请号：PCT/US2013061927

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  KOHLENBERG GREGORY A

    IPC: F02C9/16 ,  F02C3/04 ,  F02C7/20 ,  F02K3/06

    CPC classification number: F02K3/075 ,  F01D21/045 ,  F02C7/32 ,  F02K1/04 ,  F05D2260/30 ,  F05D2260/311 ,  Y10T29/49245

    Abstract: A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage a secondary nozzle that includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700.

    Abstract translation: 所公开的示例齿轮涡轮风扇发动机包括风扇部分，该风扇部分包括围绕轴线可旋转的多个风扇叶片和围绕发动机轴线限定的核心发动机部分。 核心发动机部分包括主喷嘴，该主喷嘴包括在主喷嘴后缘处的主外径和在主后缘的前方的主最大内径。 旁通通道是次级喷嘴，其包括次级喷嘴后缘处的外径和次级后缘前方的次级最大内径。 主喷嘴的最大内径与主喷嘴的后缘处的外径之间的比率以及次级后缘的最大内径与次级喷嘴的后缘处的外径之间的比率都是 小于约0.700。

    GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE
    4.
    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。

    5.
    发明专利
    未知

    公开(公告)号：DE69934757T2

    公开(公告)日：2007-04-26

    申请号：DE69934757

    申请日：1999-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  KOHLENBERG GREGORY A ,  LORD WESLEY K

    IPC: F02C7/045 ,  F02K1/46 ,  F02K1/38 ,  F02K1/48 ,  F02K3/02

    Abstract: The jet noise suppressor includes a nozzle (20; 30), having an arrangement thereon of trapezoidal tabs (40) disposed on the downstream end of the nozzle (20; 30), the tabs (40) having a length (L) and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

    9.
    发明专利
    未知

    公开(公告)号：DE69934757D1

    公开(公告)日：2007-02-22

    申请号：DE69934757

    申请日：1999-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  KOHLENBERG GREGORY A ,  LORD WESLEY K

    IPC: F02C7/045 ,  F02K1/46 ,  F02K1/38 ,  F02K1/48 ,  F02K3/02

    Abstract: The jet noise suppressor includes a nozzle (20; 30), having an arrangement thereon of trapezoidal tabs (40) disposed on the downstream end of the nozzle (20; 30), the tabs (40) having a length (L) and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

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