METHODS FOR CALCULATING THE THERMAL AND STRESS-STRAIN CONDITIONS OF THE MAIN COMBUSTION CHAMBERS FLAME TUBES

Abstract

Large-scale russian aggression has created a number of new and critical challenges in the field of security and defense. The growing number of emerging tasks, and at the same time the need for greater efficiency in solving them, determine the need to update and implement rational ways to maintain the serviceability of the required number of aircraft, taking into account their own and international experience. Thus, the development of a scientific and methodological apparatus for modeling physical processes that occur in resource-limiting parts and assembly units of aircraft engines, regarding their impact on the durability of the material in the process of operating factors, is an urgent scientific task. At the same time, it is taken into account that absolutely every engine loading cycle during flight or ground testing corresponds to a certain proportion of damage to its components, which determines a certain quantitative measure of their exhaustion of the resource. The article proposes a methodology for calculating the thermal stress-strain states of the flame tubes of the main combustion chambers. The objectivity and accuracy of the calculations is determined by the reliability of the boundary conditions required to solve the non-stationary thermal conductivity equation. The proposed technique allows to take into account the distribution of temperature fields obtained due to numerical modeling of the working process in the main modes of engine operation.