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The blade in question has fractured at the stem by overload. There were no evidences of delayed failure like fatigue. No metallurgical and/or mechanical abnormalities were responsible for the failure. Over-tightening of the nut appears to be the most probable reason for the failur
Two damaged I stage compressor rotor blades along with two locking pins belonging to an aeroengine w...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
The blade in question has fractured at the stem by overload. There were no evidences of delayed fai...
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 ...
Fractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the l...
Fractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the l...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Cracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis sho...
Cracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis sho...
AbstractThe stage II compressor stator blade of a developmental gas turbine engine was found damaged...
All the compressor stator blades of aeroengine referred to the laboratory were found to have failed ...
The root portion of a fractured 5th stage compressor rotor blade along with two other blades pertain...
Two damaged I stage compressor rotor blades along with two locking pins belonging to an aeroengine w...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
The blade in question has fractured at the stem by overload. There were no evidences of delayed fai...
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 ...
Fractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the l...
Fractured 1st stage compressor blade and LPTR shaft belonging to an aeroengine were brought to the l...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Cracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis sho...
Cracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis sho...
AbstractThe stage II compressor stator blade of a developmental gas turbine engine was found damaged...
All the compressor stator blades of aeroengine referred to the laboratory were found to have failed ...
The root portion of a fractured 5th stage compressor rotor blade along with two other blades pertain...
Two damaged I stage compressor rotor blades along with two locking pins belonging to an aeroengine w...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
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