Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.

Abstract: One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.

Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.

Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.

Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.

Abstract: One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.