Abstract
In aircraft gas turbine engine, the rotating turbine disc is highly stressed component. The demand of high strength to weight ratio for each component of aeroengine makes the disc, a critical component from design point of view. Burst of rotor disc is one of the catastrophic failure mode of gas turbine engine. The present paper, therefore, deliberates the burst of rotating turbine disc due to overspeed. A typical gas turbine disc is modeled and elastic-plastic analysis is carried out by linearly increasing the speed. Finite element technique has been used for the analysis. The burst criteria is proposed based on the deformation taking place in the disc. A safe permissible speed between burst rotation speed and maximum allowable speed of the turbine disc is also identified as per federal aviation regulations.
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