| 摘要 |
A gas turbine engine casing includes a cavity 10 separated from the main flow 12 through the engine by an annular array of tip treatment bars 16. The tip treatment bars 16 are hollow which enables the bars to deform or break upon impact by a shed blade 4 or blade fragment. This allows the blade or blade fragment to pass through the tip treatment bars 16. Blade or blade fragments may then be contained within the cavity 10, or embedded in the casing 2, so preventing further damage to the engine. Entire blades, or large blade fragments, may be able to break through the tip treatment bars 16 and through the engine casing 2 so as to leave the engine entirely, causing the minimum of damage.The interiors of the tip treatment bars may be filled with a damping material, to minimize high cycle fatigue failure.
|
