FIELD: motors and pumps.
SUBSTANCE: invention relates to turbine blades and, particularly to modification of rear root walls to reduce mechanical stresses. Turbine blade includes aerodynamic section and root section with horizontal base frame, being displaced in radial direction between them. Root section is provided with front root wall and rear root wall. Rear root walls convexly deflected from one side to the opposite side of blade. Internal cooling circuit includes multiple set of hollows being displaced in the aforesaid root section and the aforesaid aerodynamic surface. One of the hollows is near the rear wall of root. The aerodynamic surface section has front and rear edge overhanging rear wall of root.
EFFECT: reduced stress near rear edge of aerodynamic surface if proper wall thickness is maintained between blade hollows and rear root wall.
9 cl, 6 dwg
