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    • 73. 发明授权
    • Axial compressor
    • 轴流压缩机
    • US09303656B2
    • 2016-04-05
    • US13272635
    • 2011-10-13
    • Yasuo TakahashiChihiro Myoren
    • Yasuo TakahashiChihiro Myoren
    • F04D29/32F04D29/54
    • F04D29/324F04D29/542F04D29/544F05B2240/123F05B2240/301Y10T29/49316
    • An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.
    • 轴向压缩机包括附接到限定环形流动路径的壳体的内表面的多个定子叶片和附接到限定环形流动路径的旋转转子的多个转子叶片。 在定子叶片的压力表面和定子叶片的吸力表面之间限定流动路径,叶片彼此周向相邻,或在转子叶片的压力表面和转子叶片的吸力表面之间, 叶片彼此周向相邻。 流路形成为在轴向弦长的50%的上​​游侧设置流路宽度最小的喉部。
    • 74. 发明授权
    • Transonic blade
    • 跨音速刀片
    • US09279329B2
    • 2016-03-08
    • US13879084
    • 2010-10-18
    • Chihiro MyorenYasuo TakahashiShinya Marushima
    • Chihiro MyorenYasuo TakahashiShinya Marushima
    • F04D29/38F01D5/14F04D21/00F04D29/32
    • F01D5/147F01D5/141F04D21/00F04D29/324F04D29/384F05D2210/30F05D2240/301F05D2240/302Y02T50/673
    • The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
    • 本发明提供一种跨音速刀片,其同时实现设计点的减震和在轴流式旋转机器中以跨音速或更高的流场工作的叶片的失速余量的改善。 刀片的每个翼展位置处的横截面表面平行于将前缘与刀片的后缘连接的交错线移动。 堆垛线向工作流体的上游侧移动。 堆叠线将叶片横截面的各重心位置从翼面方向位置的连接到旋转机械的旋转轴或外周侧壳体的轮毂横截面的顶端横截面 位于最远离轮毂横截面的翼展方向的位置上。
    • 77. 发明申请
    • Transonic Blade
    • 跨音速刀片
    • US20130259668A1
    • 2013-10-03
    • US13879084
    • 2010-10-18
    • Chihiro MyorenYasuo TakahashiShinya Marushima
    • Chihiro MyorenYasuo TakahashiShinya Marushima
    • F01D5/14
    • F01D5/147F01D5/141F04D21/00F04D29/324F04D29/384F05D2210/30F05D2240/301F05D2240/302Y02T50/673
    • The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
    • 本发明提供一种跨音速刀片,其同时实现设计点的减震和在轴流式旋转机器中以超音速或更高速度流动的叶片中的失速余量的改善。 刀片的每个翼展位置处的横截面表面平行于将前缘与刀片的后缘连接的交错线移动。 堆垛线向工作流体的上游侧移动。 堆叠线将叶片横截面的各重心位置从翼面方向位置的连接到旋转机械的旋转轴或外周侧壳体的轮毂横截面的顶端横截面 位于最远离轮毂横截面的翼展方向的位置上。