High aspect ratio blade main core modifications for peripheral serpentine microcircuits

A turbine engine component comprising:

• an airfoil portion having a pressure side wall and a suction side wall;
• a first cooling circuit embedded within said pressure side wall, said first cooling circuit having at least two passageways embedded within said pressure side wall;
• a second cooling circuit embedded within said suction side wall, said second cooling circuit having at least two passageways embedded within said suction side wall;
• at least one cooling fluid supply cavity located between said pressure and suction side walls;
• each said cooling fluid supply cavity having a first projecting portion extending between adjacent ones of said embedded passageways in said first cooling circuit and a second projecting portion extending between adjacent ones of said embedded passageways in said second cooling circuit;
• said first projecting portion being located on a first side of the cooling fluid supply cavity and a second projecting portion on a second side of said cooling fluid supply cavity opposite to said first side;
• said first projecting portion being located adjacent a leading edge of said cooling fluid supply cavity and said second projecting portion being located adjacent a trailing edge of said cooling fluid supply cavity;
• and
• each said projecting portion communicating with at least one film cooling hole.