Trailing Edge Cooling for Turbine Blade Airfoil

A gas turbine engine hollow turbine airfoil comprising:

• an outer wall surrounding a hollow interior;
• said outer wall extending radially outwardly in a spanwise direction from an airfoil platform to an airfoil tip and having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between said leading edge and said trailing edge;
• a trailing edge rib extending from said trailing edge toward said leading edge, said trailing edge rib forming a solid member between said pressure and suction sidewalls;
• a cooling fluid channel extending in the spanwise direction through said airfoil adjacent to said trailing edge rib;
• a first set of fluid chambers defining a plurality of pressure side fluid chambers formed in said trailing edge rib and extending chordwise between said cooling fluid channel and said trailing edge adjacent to said pressure sidewall;
• a second set of fluid chambers defining a plurality of suction side fluid chambers formed in said trailing edge rib and extending chordwise between said cooling fluid channel and said trailing edge adjacent to said suction sidewall;
• a plurality of film cooling holes extending from said pressure side fluid chambers to said pressure sidewall, and a plurality of film cooling holes extending from said suction side fluid chambers to said suction sidewall;
• a trailing edge discharge hole extending from each of said fluid chambers to said trailing edge;
• and
• a metering hole associated with each of said fluid chambers, each said metering hole defining a flow restriction connecting said cooling fluid channel to a respective fluid chamber.