Patent ID: 7225607

Claim:
An aircraft engine comprising at least first and second shafts assemblies concentrically arranged and independently rotatable with respect to one another, the first and second shaft assemblies including first and second shafts respectively connecting low pressure and high pressure turbine and compressor stages, the aircraft engine having a multi-purpose braking apparatus mounted to the engine axially aft of the low pressure turbine stage, the apparatus including a member adapted to impede rotation of the low pressure turbine stage in the event that the first shaft shears and a portion of the first shaft assembly moves rearwardly into contact with the member in a retracted position, the member selectively moveable into an extended position where the member engages at least one surface of the portion of the first shaft assembly to thereby impede rotation of the first shaft assembly while the first shaft is intact, and the apparatus including an actuator disposed between the member and the engine for selectively displacing said member between the retracted and extended positions.