Turbine blade cooling hole combination

A gas turbine engine comprising:

• a compressor section;
• a combustor;
• a turbine section having at least one turbine blade;
• and
• the at least one turbine blade including:
• an airfoil including a pressure side and a suction side;
• a platform including a pressure side wall and a suction side wall and having a leading edge end wall and a trailing edge end wall;
• a suction pocket positioned under the platform on the suction side;
• the suction pocket including a platform underside, and a fillet connecting said platform underside into a neck, said neck extending into a fir tree;
• and
• there being at least three cooling holes, with a first cooling hole extending from a first end in said platform underside to a second end in a top surface of said platform along a direction having a component toward said suction side wall, and having a component towards said trailing edge end wall, there being a second cooling hole extending from a first end in said platform underside, but closer to said fillet than is said first end of said first cooling hole, to a second end in said top surface along a direction having a component toward said pressure side end wall and a component toward said trailing edge, there being a third cooling hole having a first end in said fillet and extending to a second end at said top surface along a direction and having a component toward said pressure side end wall and another component towards said trailing edge end wall.