Design of rotating structures in military gas turbine engine is complex and arduous. The aero engine main discs and shafts are designed to achieve maximum operating capabilities under severe loads. The potential failures of primary rotating parts are extremely catastrophic. Hence, ignoring structural integrity aspects, results in engine failures, which is a major concern and motivation for the present paper.
In this paper structural integrity analysis using CAE are discussed for rotating components and various structural validation testing employed are highlighted. The structural integrity study carried out conforms to stipulation of MIL 5007 D/E. The validation carried out includes material characterization, cyclic spin tests, overspeed and burst speed tests. This paper also emphasizes structural integrity studies on engine main shafts, for buckling, maneuvers and blade-off loads.