FIELD: engines and pumps.
SUBSTANCE: invention relates to axial compressor rotor structural components that allow reducing overflows and swirling in the turbine impeller flow section. The impeller machine axial compressor stage impeller incorporates vanes 1, impeller disk 3, housing 4 and outer thrust bearing ring 5 and, additionally, shaped inserts 2 representing minor-elongation vanes fitted on the said outer thrust bearing ring 5 and the said disk between vanes 1.
EFFECT: lower hydraulic losses, higher pressure increase rate (πk) axial compressor efficiency.
3 dwg
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