Gas turbine engine blade containment assembly

摘要

A gas turbine engine rotor blade containment assembly ( 38 ) comprises a containment casing ( 40 ) and the containment casing ( 40 ) has a plurality of axially spaced ribs ( 66 ). The ribs ( 66 ) extend circumferentially and radially inwardly from the containment casing ( 40 ) to define a plurality of circumferentially extending grooves ( 76 ) and a perforate sheet ( 70 ) is secured to the radially inner ends ( 68 ) of the ribs ( 66 ). In the arrangement of the present invention the blade containment function and the acoustic treatment function are combined.