Platform cooling core for a gas turbine engine rotor blade

A gas turbine engine, comprising:

• a compressor section;
• a turbine section downstream from said compressor section;
• a rotor blade positioned within at least one of said compressor section and said turbine section, said rotor blade including:
• a platform;
• an airfoil that extends radially from said platform;
• a main body cooling core that extends inside said airfoil;
• a platform cooling core inside of said platform;
• a first cooling hole that extends between a mate face of said platform and said platform cooling core;
• a second cooling hole that extends between a gas path surface of said platform and said platform cooling core;
• and
• wherein said platform cooling core is fed with a cooling fluid from said main body cooling core.

A method of cooling a rotor blade of a gas turbine engine, comprising the steps of:

• communicating a cooling fluid into a platform cooling core of a platform of a rotor blade, including feeding the cooling fluid to the platform cooling core from a main body cooling core;
• expelling a first portion of the cooling fluid through a first cooling hole that extends through a mate face of the platform;
• and
• expelling a second portion of the cooling fluid through a second cooling hole that extends through a gas path surface of the platform.