![]() Finite Element Method was used to evaluate the range of stress intensity factor solutions in the blade with a half-elliptical flaw. The maximum Von - Mises stress was found at the fillet region near the root of the blade, the predicted state of stress has helped in identifying the region of singularity which may lead to crack initiation. Static stress analysis was carried out to ascertain the critical region or crack zone of the blade. This research aims at the estimation of fatigue crack growth and fatigue life of various three dimensional crack in a compressor blade considering the stress intensity factor calculations for a half-elliptical crack, subjected to centrifugal loading. This repeated loading and unloading can reduce the life of compressor blades. Gas turbine compressor blades are subjected to centrifugal, gas bending and vibratory loads. ![]() ![]() Abstract of research paper on Materials engineering, author of scientific article - L.J.
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