Cooled blade for a gas turbine engine

摘要

The blade has a foundry part (10) with a longitudinal body provided of a longitudinal cavity (10C) with two openings at its ends. A longitudinal bracket (30) is mounted in the cavity and has an end portion (30I). The portion and a guide way (10G) are in contact and sliding with each other through surfaces. A sealed insert is placed between the portion and a wall of one opening to integrate the insert to the bracket. An independent claim is also included for a method of manufacturing a nozzle blade of a gas turbine engine.