FORMED GAS TURBINE ENGINE SHROUD

摘要

An apparatus is disclosed that includes a formed shroud ring configured to be disposed in a gas turbine engine and extending in a circumferential direction about an airfoil member and having an integral first portion and a second portion and a yielded material region between the first portion and the second portion, the first portion bent relative to the second portion to form a bent area, and wherein the yielded material region extends substantially through a thickness of the bent area.