| 摘要 |
<p>A fan containment case assembly (30) of a gas turbine engine (10) includes a blade tip bearing liner (54) disposed therein. In the event of a fan blade loss, the bearing liner allows for circumferential movement of the fan blade tips (38) around the fan case (42). Thus, the liner reduces the destructive cutting away of the fan case, minimizing damage to the fan case and decreasing torque loading of the fan case from rotor deflections. <IMAGE></p> |
