DYNAMICS OF ROTOR SYSTEMS OF GAS TURBINE ENGINES OF AIRCRAFT WITH ELASTIC-DAMPING BEARINGS

Abstract

The paper considers the analysis of the problem of dynamic behavior of rotary systems (RS) of aviation gas turbine engines (GTE) under abnormal operating conditions, for example, in the form of a fan blade breakage. In particular, the problem of compensation (damping) of an increase in the vibration level of the rotor system of the gas turbine engine, which occurs both under the influence of the unacceptable level of imbalance obtained by the rotor, in this case, and the operation of the rotor in the flexible shaft mode, is considered. The vibrations of the RS depend on the dynamic characteristics of the stiffness and damping of their supports. That is, one of the ways to solve this problem is to use elastic-damper supports and control their operation. The purpose of this study is to study the prospects for obtaining a solution to the presented problem, where, along with the analysis of the existing design of elastic-damper supports, for the development of this direction, it is assumed to use modern computer technologies based on the finite element method (FEM) with the solution of the contact problem of elasticity theory for dynamic RS with prefabricated support structures. The paper also presents elastic-damping supports of existing aviation gas turbine engines. Their main functional purpose is to improve the vibration state of the engine. In this paper, the task for them is to develop measures aimed at implementing an additional functional purpose, consisting in controlling the dynamic state of the rotor system in abnormal modes of its operation.