A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial dir
A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are 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 its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side.
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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
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; andthe 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. 2. The guide blade as recited in claim 1 wherein the first, radially inner subsection extends between approximately 0% and approximately 40% of the radial length of the blade, viewed from radially inwardly to radially outwardly. 3. The guide blade as recited in claim 1 wherein the second, radially outer subsection extends between approximately 15% and approximately 60% of the radial length of the blade, viewed from radially inwardly to radially outwardly. 4. The guide blade as recited in claim 1 wherein the radially outer section extends between approximately 40% and approximately 100% of the radial length of the blade, viewed from radially inwardly to radially outwardly.
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이 특허에 인용된 특허 (2)
Shahpar, Shahrokh; Taylor, Mark D, Guide vane for a gas turbine engine.
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