Trailing edge cooling circuit for turbomachine airfoil

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 compressor section or the turbine section, the rotor blade including a shank portion and an airfoil extending from the shank portion, the airfoil comprising:
• a leading edge,
• a trailing edge,
• a pressure side wall extending between the leading edge and the trailing edge, and
• a suction side wall extending between the leading edge and the trailing edge, the pressure side wall and the suction side wall define a main body region and a trailing edge region, the main body region extending from the leading edge to the trailing edge region and the trailing edge region extending from the main body region to the trailing edge;
• wherein the main body region defines an upstream plenum extending along a span of the airfoil;
• and
• wherein the trailing edge region defines a plurality of pressure side channels and a plurality of suction side channels in fluid communication with the upstream plenum and arranged in a trussed structure;
• wherein the plurality of pressure side channels is disposed adjacent to the pressure side wall, and the plurality of suction side channels is disposed adjacent to the suction side wall;
• wherein the trussed structure formed by the plurality of pressure side channels and the plurality of suction side channels are partially defined by shared walls of the plurality of pressure side channels and the plurality of suction side channels;
• and wherein the shared walls extend from the pressure side wall to the suction side wall.