Turbine nozzle with trailing edge convection and film cooling

A turbine nozzle segment, comprising:

• an arcuate outer band;
• an arcuate inner band;
• and
• at least one airfoil disposed between said inner and outer bands, said airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge thereof, said airfoil comprising:
• an array of radially-spaced apart, longitudinally-extending partitions defining a plurality of cooling channels therebetween;
• a plurality of aft pins disposed in of at least one of said cooling channels and extending between said pressure and suction sidewalls;
• a plurality of elongated turbulators disposed in at least one of said cooling channels, said turbulators oriented at an angle to said longitudinal axis such that an aft end of each of said turbulators is closer to an adjacent partition than a forward end of said turbulator;
• and
• an array of radially-spaced apart, longitudinally-extending dividers defining a plurality of trailing edge slots therebetween, each of said trailing edge slots having an inlet in fluid communication with said trailing edge cavity and an axially-downstream exit;
• wherein an exposed first land extends downstream from each of alternate ones of said dividers.