| 摘要 |
A turbomachine has, on its inner casing ( 5 ) and on its shaft, recesses into which shrouds of rotor blades and/or of guide vanes ( 2 a) protrude. The recesses are configured with wave-shaped contouring arrangements ( 10 ), which extend over their periphery. The contouring ( 10 ) extends over axially extending regions of the recess and consists of periodic elevations and depressions ( 14, 15 ) in the radial direction. They can also be effected on the radially extending regions of the recess and on the shrouds. The undulation-shaped contouring arrangements are used to counteract existing pressure fields and to reduce performance losses due to mixing processes between the leakage flow and the main flow.
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