Ceramic matrix composite component cooling

A turbine nozzle segment for a gas turbine engine, the turbine nozzle segment comprising:

• an inner band defining an inner band cavity for receipt of a cooling fluid and an inner band aperture extending from the inner band cavity through the inner band;
• an outer band;
• a ceramic matrix composite (CMC) airfoil extending from the inner band to the outer band, the CMC airfoil including
• opposite pressure and suction sides extending radially along a span, the pressure and suction sides defining an outer surface of the CMC airfoil,
• opposite leading and trailing edges extending radially along the span, the pressure and suction sides extending axially between the leading and trailing edges, the leading edge defining a forward end of the CMC airfoil, the trailing edge defining an aft end of the CMC airfoil, and
• a trailing edge portion defined adjacent the trailing edge at the aft end;
• and
• an inner band cooling passage extending through the CMC airfoil from an inlet defined adjacent the inner band aperture to an outlet defined in the outer surface,
• wherein the inner band aperture and the inlet of the inner band cooling passage are aligned to provide the cooling fluid from the inner band cavity to the inner band cooling passage.