Cooling circuit having a bypass conduit for a turbomachine component

A turbomachine component includes a platform, a shank, and an airfoil. The platform includes a pressure side slash face and a suction side slash face. The shank extends radially inward from the platform. The airfoil extends radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge of the airfoil. The cooling circuit further includes at least one bypass conduit that extends from an inlet disposed in the cooling circuit to an outlet positioned on the pressure side slash face. The at least one bypass conduit being positioned radially inward of the plurality of exit channels.