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    ROTOR AIRFOILS TO CONTROL TIP LEAKAGE FLOWS
    1.
    发明申请
    ROTOR AIRFOILS TO CONTROL TIP LEAKAGE FLOWS 审中-公开
    转子空气控制提升泄漏流量

    公开(公告)号：WO9614494A3

    公开(公告)日：1997-02-13

    申请号：PCT/US9513402

    申请日：1995-10-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SHARMA OM P ,  STAUBACH JOSEPH BRENT ,  STETSON GARY

    IPC: F01D5/14 ,  F01D5/20

    CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D5/145

    Abstract: A rotor blade (24) for a gas turbine engine includes a bowed surface (43) on a tip region (40) of the suction side (32) thereof. The curvature of the bowed surface (43) progressively increases toward the tip (36) of the blade (24). The bowed surface (43) results in a reduction of tip leakage through a tip clearance (50) from the pressure side (30) to the suction side (32) of the blade (24) and reduces mixing loss due to tip leakage.

    GEARED TURBOFAN WITH THREE TURBINE SECTIONS
    2.
    发明申请
    GEARED TURBOFAN WITH THREE TURBINE SECTIONS 审中-公开
    具有三个涡轮机部分的齿轮涡轮机

    公开(公告)号：WO2015112231A3

    公开(公告)日：2015-11-12

    申请号：PCT/US2014064490

    申请日：2014-11-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  STAUBACH JOSEPH BRENT

    IPC: F02C3/073 ,  F02K3/06

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

    Abstract: A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flow into a core engine where it reaches an upstream compressor rotor. The upstream compressor rotor is configured to be driven through a second shaft by an intermediate turbine rotor. A downstream compressor rotor is configured to be driven by an upstream turbine rotor through a third shaft. An overall pressure ratio across the upstream and downstream compressor rotors is greater than or equal to about 35.0 and less than or equal to about 75.0.

    Abstract translation: 燃气涡轮发动机包括风扇转子，该风扇转子构造成由风扇驱动涡轮机通过第一轴和齿轮减速器驱动。 风扇转子被配置为将空气作为旁路空气输送到旁通管道中，并且将核心气流输送到核心发动机中，在那里它到达上游压缩机转子。 上游压缩机转子构造成通过中间涡轮机转子驱动通过第二轴。 下游压缩机转子构造成由上游涡轮转子通过第三轴驱动。 上游和下游压缩机转子之间的总压力比大于或等于约35.0且小于或等于约75.0。

    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE
    3.
    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：WO2015105594A3

    公开(公告)日：2015-10-15

    申请号：PCT/US2014067529

    申请日：2014-11-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  STAUBACH JOSEPH BRENT

    IPC: F02C3/04 ,  F02C3/06

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is 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机上游的第一涡轮机和位于第一涡轮机和第二涡轮机下游的第三涡轮机。 一台风机和三台压缩机，上游的一台压缩机与风机转子连接在一起，第三台涡轮机通过减速机驱动上游压缩机和风机。 第二中间压缩机由第二中间涡轮转子驱动，并且第一和第二压缩机下游的第三压缩机由第一涡轮转子驱动。

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