Add to ORKGCracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis showed that the blades have cracked by fatigue at the undercut of the hub. The reason for the fatigue crack initiation appears to be due to high stress concentration at the sharp edge of the undercut provided at the hub of the blade
AbstractThe stage II compressor stator blade of a developmental gas turbine engine was found damaged...
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...
Cracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis sho...
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...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
All the compressor stator blades of aeroengine referred to the laboratory were found to have failed ...
Cracked and fractured stator blades of an aeroengine were sent to the laboratory for analysis. Fract...
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 ...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
Blade No. 192 of the 1st stage compressor rotor of an aeroengine had failed by fatigue. The fatigue ...
Blade No. 192 of the 1st stage compressor rotor of an aeroengine had failed by fatigue. The fatigue ...
AbstractThe stage II compressor stator blade of a developmental gas turbine engine was found damaged...
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...
Cracked compressor stator blades of Stage I and II of an aeroengine have been analyzed. Analysis sho...
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...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
All the compressor stator blades of aeroengine referred to the laboratory were found to have failed ...
Cracked and fractured stator blades of an aeroengine were sent to the laboratory for analysis. Fract...
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 ...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
The stator blade in question has failed by fatigue. There was multiple fatigue crack initiation on t...
Blade No. 192 of the 1st stage compressor rotor of an aeroengine had failed by fatigue. The fatigue ...
Blade No. 192 of the 1st stage compressor rotor of an aeroengine had failed by fatigue. The fatigue ...
AbstractThe stage II compressor stator blade of a developmental gas turbine engine was found damaged...
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...