Gas turbine engines with improved leading edge airfoil cooling

A gas turbine engine, comprising:

• a compressor section configured to receive and compress air;
• a combustion section coupled to the compressor section and configured to receive the compressed air, mix the compressed air with fuel, and ignite the compressed air and fuel mixture to produce combustion gases;
• and
• a turbine section coupled to the combustion section and configured to receive the combustion gases, the turbine section defining a combustion gas path and comprising a turbine rotor positioned within the combustion gas path, the turbine rotor comprising
• a platform at least partially defining the combustion gas path;
• and
• an airfoil extending from the platform, the airfoil including
• a body comprising a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface;
• an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage,
• wherein the internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge;
• a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage;
• and
• a second plurality of grooves formed in the second interior surface, each of the second plurality of grooves extending in the chordwise direction within the leading edge chamber.