| 摘要 |
FIELD: machine building.SUBSTANCE: invention relates to a compressor rotating blade (10) for axial flow compressors with preferably stationary gas turbines. To minimise losses in a radial clearance a centreline (32) of located on the top of the airfoil side (30) of the airfoil (12) of the compressor rotating blade (10) have at least two bending (36, 38) points. Due to two bending points (36, 38) for the suction side circuit (42) at the section covering 35-50 % of length of the chord of the section profile (D) of the suction side circuit which is concave, and for the pressure side circuit (40) the section (E) of the pressure side circuit, which is convex.EFFECT: due to the geometry the possibility of vortex generation in the clearance, resulting in smaller losses, with the purpose of increase of general efficiency fitted with these compressor rotating blades (10) of the axial compressor.17 cl, 10 dwg, 1 tbl |
