FIELD: aircraft or ground application gas turbine engines. SUBSTANCE: proposed blade of turbomachine comprises airfoil portion with leading and trailing edges, blade pressure surface and back and also lower flange, herringbone lock and elongated root in between with sealing ribs on root. Rib under trailing edge from side of pressure surface is made shortened with lock side endface tilted to axis of symmetry and connected with elongated root over cavity of lock first tooth from airfoil portion. EFFECT: improved reliability of lock of turbomachine blade owing to prevention of development of cracks on lock working surface. 2 cl, 3 dwg
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