Turbine rotor blade for a turbine section of a gas turbine

A turbine section of a gas turbine, comprising:

• a. a rotor shaft;
• b. a rotor disk coupled to the rotor shaft, the rotor disk including a slot, the rotor disk defining a cooling flow outlet that extends through the slot;
• c. a turbine rotor blade that extends radially outward from the rotor disk, the turbine rotor blade comprising:
• i. a mounting portion disposed within the slot;
• ii. an airfoil portion that extends radially outward from the mounting portion;
• iii. a cooling circuit that extends between the mounting portion and the airfoil portion, wherein the cooling circuit is in fluid communication with the cooling flow outlet;
• iv. a platform portion disposed radially between the mounting portion and the airfoil portion, the platform portion having a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls;
• and
• v. a cooling plenum defined within the platform portion, the cooling plenum further defining the cooling circuit, wherein the cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls within the platform portion.

A gas turbine, comprising:

• a. a compressor section;
• b. a combustion section disposed downstream from the combustion section;
• and
• c. a turbine section disposed downstream from the combustion section, wherein the turbine section includes a rotor shaft, a rotor disk coupled to the rotor shaft, the rotor disk defining a plurality of slots each slot having a cooling flow outlet, and a plurality of turbine rotor blades that extend radially outward from the rotor disk, each turbine rotor blade comprising:
• i. a mounting portion disposed within a corresponding slot;
• ii. an airfoil portion that extends radially outward from the mounting portion;
• iii. a cooling circuit that extends between the mounting portion and the airfoil portion, wherein the cooling circuit is in fluid communication with the cooling flow outlet;
• iv. a platform portion disposed radially between the mounting portion and the airfoil portion, the platform portion having a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls;
• and
• v. a cooling plenum defined within the platform portion, the cooling plenum further defining the cooling circuit, wherein the cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls within the platform portion.