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    GAS TURBINE ENGINE FAN BLADE AIRFOIL PROFILE
    1.
    发明申请
    GAS TURBINE ENGINE FAN BLADE AIRFOIL PROFILE 审中-公开
    燃气轮机发动机风叶风叶轮廓

    公开(公告)号：WO2014092833A3

    公开(公告)日：2014-08-14

    申请号：PCT/US2013061123

    申请日：2013-09-23

    Applicant: UNITED TECHNOLOGIES CORP ,  CHUANG SUE-LI ,  DONG YUAN ,  HINGORANI SANJAY S ,  PRASAD DILIP

    Inventor： CHUANG SUE-LI ,  DONG YUAN ,  HINGORANI SANJAY S ,  PRASAD DILIP

    IPC: F01D5/14 ,  F01D5/12 ,  F02C7/00

    CPC classification number: F04D29/384 ,  F01D5/141 ,  F05D2220/36 ,  F05D2250/74 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T137/0536 ,  Y10T137/0645

    Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

    Abstract translation: 用于燃气涡轮发动机的风扇叶片包括翼型，所述翼型包括由压力侧和吸力侧连接的前缘和后缘，以提供沿径向方向延伸至尖端的外部翼型表面。 外部翼型表面基本上与由表1中列出的一组笛卡尔坐标描述的翼型的多个横截面轮廓形成。笛卡尔坐标由通过局部轴向弦伸缩的轴向坐标提供。 圆周坐标由局部轴向弦和跨度位置缩放。 局部轴向弦对应于跨度位置处的前缘和后缘之间的翼型的宽度。

    HIGH TURNING FAN EXIT STATOR
    5.
    发明公开
    HIGH TURNING FAN EXIT STATOR 审中-公开
    高转速风扇提取器

    公开(公告)号：EP2809929A4

    公开(公告)日：2015-04-15

    申请号：EP13778582

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BRILLIANT LISA I ,  ROSE BECKY E ,  DONG YUAN ,  BALAMUCKI STANLEY J

    IPC: F02K3/072 ,  F02C7/36

    CPC classification number: F01D5/141 ,  F02C7/36 ,  F02K3/072 ,  F05D2220/36 ,  Y02T50/673

    Abstract: A turbine engine includes a fan section that rotates about a longitudinal axis and a compressor section. The turbine engine also includes a fan exit stator located between the fan section and the compressor section, the fan exit stator including an airfoil. The airfoil defines an entrance angle with respect to a leading edge of the airfoil and a line parallel to the longitudinal axis, and the airfoil defines an exit angle with respect to a trailing edge of the airfoil and a line parallel to the longitudinal axis. A difference between the entrance angle and the exit angle is between about 45° and about 65°. The turbine engine also includes a turbine section, and a portion of the compressor section is driven by a portion of the turbine section.

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