FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: invention relates to fans and compressors of gas-turbine engines. Channel 20 for gas flow has blades 16 spaced over circumference in axial direction, leading and trailing edges 28, 30 and outer and inner tips 32, 34 also spaced radially. Outer wall 36 overlaps outer tips of blades, and inner wall 38 overlaps inner tips. One of walls has groove 40 adjoining leading edges for local increase of flow section area.
EFFECT: improved reliability of operation.
24 cl, 7 dwg
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