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Originally posted by HowardRoark
Again, let me reiterate, this was not a piston engine, it was a turbine. These are nothing like the piston engine blocks in your minivan.
Furthermore, at operating speeds, a small piece of debris can cause enormous damage (called FOD for foreign object damage). Remember that the concord was downed by FOD.
Examination of the engine a Pratt & Whitney Canada PT6A-114A, S/N PC0710, found severe impact damage.
The engine was broken into two sections and separated from the airframe.
Examination of the engine a Pratt & Whitney Canada PT6A-114A, S/N PC0710, found severe impact damage. Only the power section and part of the gas generator was recovered. The constant speed unit, fuel control unit and fuel pump were not recovered. The compressor turbine stators were found bent in the direction of rotor rotation. The first and second stage compressor rotors were not recovered. The engine power section including the reduction gearbox and gas generator was recovered intact. The compressor intake case and remaining engine including the accessory gearbox and accessories were not recovered. The engine displayed impact damage at the 4 o'clock position on the exhaust case in the area of the flange. The propeller shaft was intact and seized. The exhaust duct displayed severe impact deformation with a significant portion detached. The gas generator case displayed evidence of structural compression and buckling. The compressor section was exposed as recovered. The 1st and 2nd stage compressor rotors were not recovered. The 3rd stage compressor rotor was missing all blades except one which was found lodged in the 2nd stage stator. The impeller was intact with nicks on the leading edge. The 1st and 2nd stage compressor stators were intact and found bent in the direction of rotor rotation. the 3rd stage stator was found intact with minor damage to the leading edge. The 2nd and 3rd stage spacers were found intact. The 1st stage spacer was missing. The tie rods were fractured in the region of the 1st stage rotor. The compressor inlet case and remaining engine was detached at the flange attachment to the gas generator case. The compressor shroud displayed circumferential rubbing due to compressor rotor blades making radial contact. Examination of the power turbine as viewed through the exhaust duct showed several blades fractured near the tip. The blades remained attached to the power turbine disk. Examination of the engine revealed that the damage noted was consistent with the engine making power at time of the accident.