Add to ORKGThree blades withdrawn from the 2nd stage of an aeroengine were received for analysis. Fractographic examination revealed that one of the blades had failed by fatigue. Based on the observations and analysis, it appears that the fatigue crack had initiated at a foreign object damage on the concave side of the airfoil. The microstructure and chemical composition of the blade material were found to conform to specification
In spite of the high levels of reliability of modern aeroengine components resulting from rigid stan...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
Four 2nd stage rotor blades belonging to different melts, which failed during fatigue testing, were ...
Three failed compressor rotor blades, one from first stage and the other two from second stage, bel...
Three failed compressor rotor blades, one from first stage and the other two from second stage, bel...
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 ...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
The compressor rotor blade in question had failed by fatigue. There were two fatigue cracks in the a...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Four 2nd stage rotor blades belonging to different melts, which failed during fatigue testing, were ...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
In spite of the high levels of reliability of modern aeroengine components resulting from rigid stan...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
Four 2nd stage rotor blades belonging to different melts, which failed during fatigue testing, were ...
Three failed compressor rotor blades, one from first stage and the other two from second stage, bel...
Three failed compressor rotor blades, one from first stage and the other two from second stage, bel...
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 ...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
The compressor rotor blade in question had failed by fatigue. There were two fatigue cracks in the a...
There was an incidence to an aircraft wherein the pilot heard a loud bang on accelerating throttle t...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
Two compressor stator blades from Stages I and II of an aeroengine were sent to the laboratory for i...
Four 2nd stage rotor blades belonging to different melts, which failed during fatigue testing, were ...
Two cracked blades belonging to first stage compressor of an aeroengine were forwarded to the labora...
In spite of the high levels of reliability of modern aeroengine components resulting from rigid stan...
The damaged/failed compressor stator and rotor blades of an aeroengine were analyzed. All the blades...
Four 2nd stage rotor blades belonging to different melts, which failed during fatigue testing, were ...