A turbomachine component, comprising: a platform, the platform having a leading platform face, a trailing platform face, and a platform surface; a shank extending radially inward from the platform, wherein the shank includes a suction-side slash face circumferentially separated from a pressure-side slash face; an airfoil extending radially outward from the platform, the airfoil including a leading edge and a trailing edge; a cooling circuit defined within the shank, the platform and the airfoil, the cooling circuit comprising: a plurality of pins extending across the cooling circuit, the plurality of pins including a first pin group positioned radially inward of the platform surface and a second pin group positioned within the airfoil downstream from the first pin group with respect to the direction of coolant flow within the cooling circuit; a plurality of exit channels disposed along the trailing edge of the airfoil downstream from the plurality of pins; and at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face, the at least one bypass conduit being positioned radially inward of the platform surface, wherein the at least one bypass conduit extends from the inlet, towards the suction-side slash face, to the outlet, and wherein the inlet is disposed upstream of the first pin group with respect to the direction of coolant flow within the cooling circuit, in a shank portion of a trailing edge passage of the cooling circuit. a platform, the platform having a leading platform face, a trailing platform face, and a platform surface; a shank extending radially inward from the platform, wherein the shank includes a suction-side slash face circumferentially separated from a pressure-side slash face; an airfoil extending radially outward from the platform, the airfoil including a leading edge and a trailing edge; a cooling circuit defined within the shank, the platform and the airfoil, the cooling circuit comprising: a plurality of pins extending across the cooling circuit, the plurality of pins including a first pin group positioned radially inward of the platform surface and a second pin group positioned within the airfoil downstream from the first pin group with respect to the direction of coolant flow within the cooling circuit; a plurality of exit channels disposed along the trailing edge of the airfoil downstream from the plurality of pins; and at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face, the at least one bypass conduit being positioned radially inward of the platform surface, wherein the at least one bypass conduit extends from the inlet, towards the suction-side slash face, to the outlet, and wherein the inlet is disposed upstream of the first pin group with respect to the direction of coolant flow within the cooling circuit, in a shank portion of a trailing edge passage of the cooling circuit. a plurality of pins extending across the cooling circuit, the plurality of pins including a first pin group positioned radially inward of the platform surface and a second pin group positioned within the airfoil downstream from the first pin group with respect to the direction of coolant flow within the cooling circuit; a plurality of exit channels disposed along the trailing edge of the airfoil downstream from the plurality of pins; and at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face, the at least one bypass conduit being positioned radially inward of the platform surface, wherein the at least one bypass conduit extends from the inlet, towards the suction-side slash face, to the outlet, and wherein the inlet is disposed upstream of the first pin group with respect to the direction of coolant flow within the cooling circuit, in a shank portion of a trailing edge passage of the cooling circuit.