| 摘要 |
<p>The invention relates to a method for profiling a replacement blade (1) for an axial turbomachine, comprising the steps of: measuring the hub contour geometry (5) and the housing contour geometry (6) of the flow channel of the old blade (11), as well as the axial position of the centre of gravity of the blade aerofoil of the old blade (11); laying out the geometry of the blade aerofoil (2) of the replacement blade (1), said blade aerofoil (2) having a rearward sweep (14) on its leading edge (7); defining a region (21) of the blade aerofoil (2) which is near the mounting and in which the positive influence of the rearward sweep (14) on the degree of stage efficiency is rated as low; and axially displacing the replacement blade (1) aerofoil section that is arranged outside this region (21) in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil (2) of the replacement blade (1) coincides with that of the old blade (11). In the region (21) from the mounting-side section (5) to the displaced blade aerofoil section of the replacement blade (2), the leading edge (7) is inclined downstream towards the mounting such that the blade aerofoil (2) has a transition sweep (19) in this region (21).</p> |
