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    • 9. 发明申请
    • GAS TURBINE ENGINE AIRFOIL PROFILE
    • 燃气轮机发动机翼型轮廓
    • WO2015112222A2
    • 2015-07-30
    • PCT/US2014/063865
    • 2014-11-04
    • UNITED TECHNOLOGIES CORPORATION
    • PONS, David M.RAMIREZ, Loubriel
    • F01D9/02F01D5/14
    • F01D5/141F01D9/02F01D9/041F02C3/04F05D2220/32F05D2240/12F05D2250/711F05D2250/74F05D2260/202Y02T50/672Y02T50/673
    • An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. 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 scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to ±0.050 inches (±1.27 mm).
    • 示例性翼型件包括翼型体,翼型体具有由压力侧和吸力侧连接的前缘和后缘,以提供从至少一个平台沿径向方向延伸的外部翼面。 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一致地形成。笛卡尔坐标由轴向坐标提供,轴向坐标由局部轴向弦标度,圆周坐标 由一个局部轴向弦和一个跨度位置缩放。 局部轴向弦对应于跨度位置处前缘和后缘之间的翼型宽度,并且表1中的笛卡尔坐标具有相对于指定坐标的公差,其高达±0.050英寸(±1.27 毫米)。