Patent ID: 6637186
Filing Date: 2003-10-28
Classification: F01D

Abstract:
A gas turbine engine disposed about a longitudinal axis, the gas turbine engine having a rotor and a stator, the rotor including a fan, the fan having a plurality of blades mounted thereon, the stator including a fan case disposed radially outward of the fan, wherein the improvement is characterized by:a segmented hardened liner disposed in the fan case to circumscribe the fan blades for minimizing the damage to the fan case during a fan blade loss condition by allowing the fan blades to skid along the segmented liner and for precluding the embedding of the blades in the fan case to minimize unwanted torque loading of the fan case, with the hardened liner being harder that the fan blade tip material; wherein by the segmented hardened liner includes a plurality of plate shingles circumferentially disposed in the fan case, each of the plurality of the shingles being offset from adjacent shingles and forming an overlap region between the adjacent shigles.