Patent ID: 7094029

Claim:
A method for assembling a gas turbine engine compressor including a stator assembly and a rotor assembly, said method comprising: providing a casing formed from a plurality of rings; coupling a first of the casing rings around the rotor assembly such that a radially inner surface of the first casing ring is axially aligned with, and radially outward from, a row of rotor blades extending from the rotor assembly, wherein the first casing ring includes a ligament portion including a plurality of circumferentially spaced ligaments and a plurality of circumferentially-spaced ligament openings adjacent each of the ligaments, wherein the first casing ring includes at least one relief cut that extends from the radially inner surface to the ligament openings; and coupling a second of the casing rings to the first casing ring with a fastener assembly, such that the first casing ring radially inner surface facilitates insulating the fastener assembly from the compressor flowpath.