Combined gas turbine engine blade containment assembly and acoustic treatment

摘要

A gas turbine engine rotor blade containment assembly 38 comprises a containment casing 40 having a plurality of axially spaced ribs 66. The ribs 66 extend radially inwardly from the containment casing 40 to define a plurality of circumferentially extending grooves 76. A perforate sheet 72 is secured to the radially inner ends 68 of the ribs 66 and may be brazed, diffusion bonded or adhesively bonded to the ribs 66. Axially extending members (74, Fig 4) may be secured between each pair of adjacent ribs 66. The ribs 66 may have uniform or decreasing thickness in the radial direction and may be integral with the casing 40. The ribs 60 may be arranged on a downstream portion of the containment casing 40.