method for insertion of a innenteils in a gasturbinenschaufel

摘要

An insert (70) containing apertures for impingement cooling a nozzle vane of a nozzle segment in a gas turbine is inserted into one end of the vane (16). The leading end (76) of the insert is positioned slightly past a rib (74) adjacent the opposite end of the vane through which the insert is inserted. The end of the insert is formed or swaged into conformance with the inner margin of the rib. The insert is then brazed or welded to the rib. IMAGE