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Aero engine rotor burst evaluation is one of the most important problems to be taken care off, whenever it comes todesigning a turbo machinery disc. The consequences of a failure can be intense, since the disc fragments into multiplepieces and they are hurled away in all the possible direction at high speeds. Due to high thermo-mechanical loadingconditions the disc is subjected to varying degrees of temperature from bore to rim. However, the centrifugal forcedominates in the disc which ranges from 80%-90% and the rest can be treated as thermal and gas loads. Thechallenge lies at designing a disc for off-design conditions with their varying loads and duty cycles. In present workevaluation of safety limits and low-cycle fatigue (LCF) life estimation of an aero engine disc through classicalmethods and blending the terminologies with simulation engineering to arrive at a probable interpretation ofnumber of duty cycles is carried out. The methodology compares the fatigue parameters involved in evaluation of disclife at off-design condition through sensitivity analysis. The design tool closely connects the flight certification FAAand EASA the regulating agencies for safety in air transportation vehicles. The off-design speed regulations throughAPI and MIL handbook for material specification are considered to carry out design of experiments using finiteelement analysis approach

Verification of Over-Speed and Burst Margin Limits in Aero Engine Disc along with Low Cycle Fatigue Life