Gas turbine engines with turbine 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 leading edge, a trailing edge, and side walls defining an interior cavity, the airfoil further comprising an interior wall disposed within the interior cavity of the body and extending between the side walls to define a supply chamber and a leading edge chamber,
• wherein the interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.