FIELD: machine building.
SUBSTANCE: blade with airfoil comprises an inner platform zone and an outer tip zone in the radial direction, and a front entrance edge and a rear exit edge, between the platform zone and the tip zone, in axial direction. The blade is fitted with a pressure side being concave in the radial direction between the inner platform zone and the outer tip zone, as well as with a back being convex in the radial direction between the inner platform zone and the outer tip zone. The blade width in the axial direction between the entrance edge and the straight exit edge is changed parabolically from the maximal width in the platform and tip zones to the minimal width at the section between the platform zone and the tip zone. The other invention of the group refers to an axial turbomachine comprising the group of the above blades with airfoil.
EFFECT: invention allows for the reduction of profile losses at a blade.
15 cl, 5 dwg
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