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    • 13. 发明申请
    • Annular Flow Duct for a Turbomachine Through which a Main Flow can Flow in the Axial Direction
    • 一个涡轮机的环形流道,主流通过该流道可以在轴向流动
    • US20090290974A1
    • 2009-11-26
    • US12227928
    • 2007-05-29
    • Romain BayereMalte BlomeyerChristian CorneliusTorsten MatthiasUwe Sieber
    • Romain BayereMalte BlomeyerChristian CorneliusTorsten MatthiasUwe Sieber
    • F04D27/02F04D29/68
    • F01D5/145F01D5/143F04D29/526F04D29/685
    • Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.
    • 公开了一种用于涡轮机的环形流动管道,该流动管道围绕沿着轴向运动的机器轴线同心地布置并且由用于引导主流量的圆形横截面的边界壁限定,其中边界壁具有多个回流 分布在其圆周上的通道,并且在每种情况下,部分流动在出口位置处与主流体分离,并且在位于排放位置上游的进给位置处返回到主流体,并且具有从根本上排列在流体中的机翼 一个叶片环的管道,其机翼尖头与边界壁相对,在每种情况下形成间隙,其中翼型件可沿着边界壁的圆周沿预定的旋转方向移动。 此外,从旋转方向观察对泵送和流动分离不敏感的压缩机,每个返回流动通道的排放位置位于相应进给位置的上游。
    • 15. 发明申请
    • METHOD FOR PROFILING A REPLACEMENT BLADE AS A REPLACEMENT PART FOR AN OLD BLADE FOR AN AXIAL-FLOW TURBOMACHINE
    • 将替代叶片分类为用于轴流式涡轮机的旧叶片的替换部件的方法
    • US20140212282A1
    • 2014-07-31
    • US14241485
    • 2012-08-14
    • Christian CorneliusTorsten Matthias
    • Christian CorneliusTorsten Matthias
    • F01D5/12B23P6/00F01D9/02
    • F01D5/12B23P6/005F01D5/141F01D5/147F01D9/02F05D2230/80Y10T29/4932
    • A method for profiling a replacement blade for an axial turbomachine is provided. The method includes: measuring hub contour geometry and housing contour geometry of the flow channel of the old blade and the axial position of the centre of gravity of the blade aerofoil of the old blade; laying out geometry of the blade aerofoil of the replacement blade, the blade aerofoil having a rearward sweep on its leading edge; defining a region of the blade aerofoil near the mounting and in which positive influence of the rearward sweep on the degree of stage efficiency is rated as low; and axially displacing the replacement blade aerofoil section arranged outside this region in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil of the replacement blade coincides with the old blade. In the region from the mounting-side section to the displaced blade aerofoil section of the replacement blade, the leading edge is inclined downstream towards the mounting such that the blade aerofoil has a transition sweep in this region.
    • 提供了一种用于对用于轴向涡轮机的替换叶片进行成形的方法。 该方法包括:测量轮毂轮廓几何形状和壳体轮廓几何形状的旧叶片的流道和叶片叶片的叶片重心的轴向位置; 布置替换叶片的叶片机翼的几何形状,叶片机翼在其前缘具有向后扫掠; 在安装附近限定叶片机翼的区域,其中向后扫掠的积极影响对于阶段效率的程度被评定为低; 并且沿上游方向轴向移动设置在该区域外的替换叶片翼型部分,直到替换叶片的叶片翼面的重心的轴向位置与旧叶片重合。 在从安装侧部分到替换叶片的移动叶片翼型部分的区域中,前缘朝向安装件向下倾斜,使得叶片翼型件在该区域中具有过渡扫掠。