| 摘要 |
A compressor casing structure in the region of a rotor blade ring through which there is an axial flow, having a multiplicity of axial grooves which extend from a first radial plane upstream of the blade-tip inlet edges into a second radial plane between the blade-tip inlet edges and the blade-tip outlet edges and have groove cross sections with parallel side walls. The center axes of the groove cross sections have, at the upstream groove ends, from the opening to the groove base, an angle of inclination with a circumferential component counter to the direction of movement of the blade. The center axes of the groove cross sections have, at the downstream groove ends, an angle of inclination with a circumferential component in the direction of movement of the blade.
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