The objective of this project is to investigate the fracture of blade roots of aeroengines subjected to cyclic loading by means of computational tools. The low pressure (LP) compressor blades are the largest blades within an aircraft gas turbine. Located at the front of the engine, the blade is assembled to a rotating disc by a dovetail joint. Dovetail joint failure is predominantly due to fretting fatigue and it is relevant because of an inadequate understanding of the contact stresses in the blade root, which results in being unable to predict when failure may occur.
Keywords: aeroengine, gas turbine, fatigue, aeroelasticity, contact, finite elements.
Please contact Dr J.L. Curiel-Sosa (email) for an informal discussion on proposed PhD research -or similar- in this field.