Trailing edge cooling circuit

A turbomachine comprising:

• a compressor section;
• a combustion section disposed downstream of the compressor section;
• and
• a turbine section disposed downstream of the combustion section, wherein a rotor blade is disposed in one of the combustion section or the turbine section, the rotor blade having an airfoil that defines a camber axis, a transverse direction orthogonal to the camber axis, and a radial direction orthogonal to the transverse direction, the airfoil comprises:
• a leading edge;
• a trailing edge;
• a pressure side wall and a suction side wall each extending between the leading edge and the trailing edge, wherein a camber axis is defined halfway between the pressure side wall and the suction side wall;
• and
• a cooling circuit defined in the airfoil, the cooling circuit having a trailing edge cooling circuit comprising a pressure side channel and a suction side channel, the pressure side channel disposed in cooling proximity to the pressure side wall and the suction side channel disposed in cooling proximity to the suction side wall;
• wherein the pressure side channel converges in cross-sectional area from a pressure side inlet to a pressure side outlet adjacent the trailing edge;
• wherein the suction side channel converges in cross-sectional area from a suction side inlet to a suction side outlet adjacent the trailing edge;
• wherein the pressure side inlet overlaps with the suction side inlet in both the radial direction and the transverse direction.