Finite Element Modeling of Contact Heat Transfer in the Turbine Rotor Design of an Aircraft Gas Turbine Engine

Abstract

On the basis of the finite element method (FEM) a mathematical model of the modular structure of the turbomachine exemplified by the aircraft gas turbine engine, AL31F, is developed. It is notable for describing the solution of interdependent problems of the theory of elasticity and thermal conductivity, taking into account the changes in the parameters of the contact interaction of the turbomachine parts. A technique allowing obtaining updated values of stress and temperature fields in the modular structure of turbomachines, operating in a complicated complex of structural-force and thermal effects, is proposed with the identification of the influence of contact thermal resistance on the temperature field.