Turbine airfoil trailing edge cooling slots

A gas turbine engine turbine airfoil comprising:

• widthwise spaced apart pressure and suction sidewalls extending outwardly along a span from an airfoil base to an airfoil tip;
• the pressure and suction sidewalls extending chordwise between opposite leading and trailing edges;
• a spanwise row of spanwise spaced apart trailing edge cooling holes encased in the pressure sidewall and ending at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge;
• the cooling hole including in downstream serial cooling flow relationship, a curved inlet, a metering section with a constant area and constant width flow cross section, and a spanwise diverging section leading into the trailing edge cooling slot;
• and
• a spanwise height substantially greater than a hole width through the cooling hole;
• at least one of the cooling holes including a raised floor extending downstream through each of the diverging sections starting at the end of the corresponding metering section and into and at least partially through the corresponding cooling slot;
• the raised floor including in downstream serial relationship a flat up ramp in the diverging section, a flat down ramp in the trailing edge cooling slot, and a transition section between the up and down ramps;
• the up ramp ramping up and extending downstream from the suction sidewall surface at the end of the metering section;
• and
• the down ramp ramping down and extending downstream from the transition section to the trailing edge.