Patent Number: 6,305,899

Title: Gas turbine engine

Abstract: A gas turbine engine core casing comprises axially adjacent portions (20,21) that are flanged to receive bolts (28) that attach the portions (20,21) to each other. One of the casing portions (20) is provided with flange (23) that is of L-shape cross-section to provide local enhancement of the rigidity of the casing portion (20). Such rigidity enhancement provides improved debris containment in the event of the failure of rotor components within the casing.

Inventors: Saunders; Duncan (Derby, GB)

Assignee: Rolls-Royce plc

International Classification: F01D 21/00 (20060101); F01D 25/24 (20060101); F01D 21/04 (20060101); F01D 021/00 (); F01D 025/24 ()

Expiration Date: 10/23/2018