Add to ORKGFractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the laboratory for analysis. Fractographic examination indicated that both the components had failed by overload due to impact. There were no evidences of delayed failure like fatigue. No metallurgical abnormalities were found responsible for the failure
Components of an aircraft which met with an accident immediately after take off were forwarded to th...
The root portion of a fractured 5th stage compressor rotor blade along with two other blades pertain...
Three blades withdrawn from the 2nd stage of an aeroengine were received for analysis. Fractographic...
Fractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the l...
The blade in question has fractured at the stem by overload. There were no evidences of delayed fai...
The blade in question has fractured at the stem by overload. There were no evidences of delayed fai...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
A damaged LP compressor stage-1 blade of aircraft was analyzed. Laboratory investigation showed evid...
A damaged LP compressor stage-1 blade of aircraft was analyzed. Laboratory investigation showed evid...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
Following an incidence in an aeroengine, two compressor stator blades belonging to stage II and III ...
Following an incidence in an aeroengine, two compressor stator blades belonging to stage II and III ...
Two damaged I stage compressor rotor blades along with two locking pins belonging to an aeroengine w...
Components of an aircraft which met with an accident immediately after take off were forwarded to th...
The root portion of a fractured 5th stage compressor rotor blade along with two other blades pertain...
Three blades withdrawn from the 2nd stage of an aeroengine were received for analysis. Fractographic...
Fractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the l...
The blade in question has fractured at the stem by overload. There were no evidences of delayed fai...
The blade in question has fractured at the stem by overload. There were no evidences of delayed fai...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
A damaged LP compressor stage-1 blade of aircraft was analyzed. Laboratory investigation showed evid...
A damaged LP compressor stage-1 blade of aircraft was analyzed. Laboratory investigation showed evid...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
Following an incidence in an aeroengine, two compressor stator blades belonging to stage II and III ...
Following an incidence in an aeroengine, two compressor stator blades belonging to stage II and III ...
Two damaged I stage compressor rotor blades along with two locking pins belonging to an aeroengine w...
Components of an aircraft which met with an accident immediately after take off were forwarded to th...
The root portion of a fractured 5th stage compressor rotor blade along with two other blades pertain...
Three blades withdrawn from the 2nd stage of an aeroengine were received for analysis. Fractographic...