| 摘要 |
The invention relates to a guide blade of a turbomachine, in particular of a compressor, wherein a blade (10) of the guide blade without an inner shroud has a flow inlet edge (12), a flow outlet edge (13), a suction side (14), and a pressure side (15), wherein the blade (10) is formed by a plurality of blade sections stacked one on the other in the radial direction, the centers of gravity of the blade sections extending along a stacking axis, and wherein the blade sections are stacked one on the other in the radial direction in such a way that, in a radially inner section (22) of the blade (11) connected to a radially outer section (20) of the blade (10), the stacking axis has the only inflection point thereof in the radial curvature thereof, namely between a first, radially inner sub-section (24) of the radially inner section (22), in which the stacking axis is curved concavely toward the pressure side, and a second, radially outer sub-section (23) of the radially inner section (22), in which the stacking axis is curved concavely toward the suction side. |
