Turbine nozzle segments and systems are provided. For example, a turbine nozzle segment comprises an airfoil extending axially between leading and trailing edges; an inner band defining a portion of a flow path inner boundary; and an outer band defining a portion of a flow path outer boundary. An airfoil trailing edge portion defines the trailing edge and extends axially beyond the inner and outer bands such that the trailing edge is defined axially aft of the inner and outer band aft ends. An exemplary turbine nozzle system comprises the turbine nozzle segment, an outer member positioned aft of the outer band at the trailing edge portion outer end to define the flow path outer boundary along the trailing edge portion, and an inner member positioned aft of the inner band at the trailing edge portion inner end to define the flow path inner boundary along the trailing edge portion.