Cooling schemes for airfoils for gas turbine engines

A gas turbine engine comprising:

• a turbine section;
• a compressor section;
• and
• an airfoil located in at least one of the turbine section and the compressor section, the airfoil comprising:
• a leading edge, a trailing edge, a pressure side exterior wall extending between the leading edge and the trailing edge and defining a pressure side, and a suction side exterior wall extending between the leading edge and the trailing edge and defining a suction side, wherein a plurality of cooling passages are formed within the airfoil;
• a plurality of first interior ribs extend from the pressure side exterior wall to the suction side exterior wall;
• and
• a plurality of second interior ribs extend from the suction side exterior wall toward the pressure side exterior wall and intersect with a first interior rib, wherein:
• at least one pressure side main body cooling passage is defined between the pressure side exterior wall and two first interior ribs of the plurality of first interior ribs, and
• at least one suction side main body cooling passage is defined between the suction side exterior wall, a first interior rib, and a second interior rib.