Patent ID: 8613592
Filing Date: 2013-12-24
Classification: F01D,F04D,F05D,Y02T

Abstract:
1. A guide blade of a compressor comprising: a blade without an inner shroud and having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side, the blade being formed by a plurality of blade sections stacked one on top of the other in a radial direction, centers of gravity of the blade sections extending along a stacking axis, the blade sections being stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has a single inflection point in a radial curvature, the single inflection point being between a first, radially inner subsection of the radially inner section and a second, radially outer subsection of the radially inner section, the stacking axis in the first, radially inner subsection having a concave curvature toward the pressure side and the stacking axis in the second, radially outer subsection having a concave curvature toward the suction side; in the first, radially inner subsection, an inclination of the stacking axis decreasing from radially outwardly to radially inwardly in such a way that in a region of a radially inner blade tip, situated at a distance from a hub of a rotor of the turbomachine by a running clearance, the stacking axis extends essentially in the radial direction; the single inflection point of the stacking axis in a radial curvature formed between the first, radially inner subsection and the second, radially outer subsection being situated between approximately 15% and approximately 40% of the radial length of the blade, viewed from radially inwardly to radially outwardly; and the stacking axis having a concave curvature toward the suction side in the radially outer section, so that the radially outer section forms or represents an extension of the second, radially outer subsection.