Verfahren zu formung von gasturbinentriebwerkskomponenten

Abstract

A method of forming a gas turbine engine component (260) according to an example of the present disclosure includes, among other things, attaching a cover skin (270) to an airfoil body (268), the airfoil body (268) and the cover skin (270) cooperating to establish pressure and suction sides (PS, SS) of an airfoil (261), positioning the airfoil (261) between first and second dies (287-1, 287-2) of a deforming station (284-2), heating the airfoil body (268) to a first predefined temperature threshold between the first and second dies (287-1, 287-2), and moving the first die (287-1) relative to the second die (287-2) to hold the airfoil (261) between the first and second dies (287-1, 287-2) subsequent to the heating step, and then deforming the airfoil (261) between the first and second dies (287-1, 287-2).