Abstract: Method of containing fractured turbine engine components, for example rotor and blade fragments within turbine engine casings, comprising diffusing and impeding motion of the fractured blade fragment by encircling the turbine engine with an honeycomb structure; shielding the honeycomb with an outer shell which has a high bending stiffness and which encloses a series of subdivided compartments in juxtaposition with the honeycomb; and absorbing energy of the fractured blade fragments by supporting a series of ceramic blocks within the confined compartments adjacent said honeycomb. A suggested ceramic for use in the blocks is a hot-pressed silicon carbide. The method is distinguished from the prior art in its ability to sustain the subsonic velocities.