Fatigue life estimation of aircraft engine compressor with suitable material selection (Analytical approach for compressor lifetime)

In Aviation sector, fatigue life and its analysis of each component is one of the prime factors of consideration due to the catastrophic failures that can result from it. Most of the components fail in high cycle fatigue regimes, but the compressor's fatigue life is intermediate between high cycle fatigue and low cycle fatigue. Objective of this paper is to estimate and compare the suitability of a centrifugal compressor in a gas turbine engine with different materials are Titanium alloy 685, Aluminium alloy 2618 and Carpenter Invar 36 alloy by calculating the displacement and fatigue life using analytical method. The reference component of this paper is modeled by using CATIA and simulation is carried through ANSYS with the property of Aluminium alloy 2618, for the purpose of validating the simulation and analytical results.