FIELD: technological processes.
SUBSTANCE: invention relates to foundry. Casting core (200) includes airfoil portion (202) having airfoil base end (208), airfoil tip end (210), concave side exterior surface (212), convex side exterior surface (214), leading edge (204), and trailing edge (206). Airfoil portion is twisted in a radial direction from the airfoil base end to the airfoil tip end. Airfoil portion includes first void (220) between the concave side exterior surface (202) and the convex side exterior surface and extending radially to define the shape of a rib of an airfoil to be cast around the core. First leading edge surface and first trailing edge surface of the void are twisted from the airfoil base end to the airfoil tip end.
EFFECT: invention can be used in the manufacture of turbine and compressor blades, turbine and compressor vanes.
19 cl, 12 dwg
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