Modelling and Analysis on the Fatigue Life of Gas Turbine Compressor Disc

Abstract

The disc itself revolves at an extremely rapid pace, putting a lot of strain on the turbine compressor disc. This exceptionally stressed part provides an impact on a particular location such as a bore, bolt hole, slot, or fillet. The bore area of the disc is an especially crucial zone, since any failure there would result in an unprecedented breakdown of the entire turbine. So in this study, the finite-element approach is employed to offer a numerical estimate of the lifespan of a gas turbine prototype disc. Engine start-up and shutdown, as well as significant throttle fluctuations during operation, can cause cyclic tensile stresses in this area. These cyclic tensile stresses will surpass the component's yield strength and may potentially induce low cycle fatigue failure. As a result, there is a need to improve the fatigue and fracture lifetime of the bore area in order to meet the expanding design life requirements.