US Patent 10301943 Turbomachine rotor blade

The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud includes first and second walls that at least partially define a cooling core fluidly coupled to the cooling passage. The rotor blade also includes a plurality of ribs positioned within the cooling core and coupled to the first and second walls. The reinforcing structure includes a plurality of interconnected ribs having a first rib with a first orientation and a second rib with a second orientation. The first and second orientations are different in three spatial dimensions.