System and method for cooling components of a gas turbine engine

A system for cooling a component of a gas turbine engine defining a radial direction, the system comprising:

• a turbine rotor blade defining a cooling passage for providing a cooling airflow through the turbine rotor blade, the cooling passage having an inlet and an outlet spaced from the inlet along the radial direction, the turbine rotor blade comprising a blade tip, the outlet of the cooling passage formed on the blade tip of the turbine blade;
• a casing spaced from the blade tip along the radial direction, the casing defining an aperture in airflow communication with the outlet of the cooling passage;
• and
• a coolant duct assembly in airflow communication with the aperture of the casing for receiving at least a portion of the cooling airflow from the outlet of the cooling passage in the turbine rotor blade and distributing the cooling airflow to the component of the gas turbine engine.