Cooling circuit for turbine component

The invention provides a rotor blade. The rotor blade includes a platform (42) and a shank (36) extending radially inward from the platform (42). The rotor blade also includes an airfoil (40) extending radially outward from the platform (42). The airfoil (40) includes a leading edge (52) and a trailing edge (54). A cooling circuit (56) is defined within the shank (36) and the airfoil (40). The cooling circuit (56) includes a plurality of pins (68). The plurality of pins (68) includes a first set of pins (72) positioned radially inward of the platform (42) and a second set of pins (74) positioned within the airfoil (40). The cooling circuit (56) also includes a plurality of outlet channels (66) disposed along the trailing edge (54). The plurality of outlet channels (66) are downstream of the plurality of pins (68). The cooling circuit (56) also includes at least one bypass conduit (88) extending from an inlet (90) disposed in the cooling circuit (56) to an outlet (92) positioned on the aft platform surface (11