Patent ID: 6409471
Filing Date: 2002-06-25
Classification: F01D,Y10T

Abstract:
A method of machining an inner surface of a shroud assembly extending generally circumferentially around a central axis of a gas turbine aircraft engine, said engine including a disk mounted inside the shroud assembly for rotation about the central axis of the engine and a plurality of circumferentially spaced rotor blades extending generally radially outward from an outer diameter of the disk, each of said blades extending from a root positioned adjacent the outer diameter of the disk to a tip positioned outboard from the root, said method comprising:determining a pre-machined radial clearance between the tips of said plurality of rotor blades and the inner surface of the shroud assembly during flight of said aircraft engine at each of a plurality of circumferentially spaced locations around the shroud assembly; and machining said inner surface of the shroud assembly based on said pre-machined radial clearances to provide a uniform post-machined radial clearance during flight between the tips of said plurality of rotor blades and the inner surface of the shroud assembly at each of said plurality of circumferentially spaced locations around the shroud assembly.