Adaptive kinematic structures for construction of an aviation gas turbine engine

Abstract

Depending on the operating conditions of a part or assembly of an aircraft gas turbine engine (GTE); various calculation schemes are used to calculate the stress-strain state, which differ in the finite element approximation method, material models, and load models. Calculation schemes for GTE design and verification calculations are determined. For the design of an aircraft engine, there must be fast and effective solutions for analyzing several design solutions in automated and optimal design systems. These schemes use theories of elasticity and small elastoplastic deformations. The calculation scheme of the problem of gas dynamics, heat conduction, and mechanics of a deformed body determines the operating conditions of the part or assembly and more complete models of physical and geometric nonlinearity. Geometric nonlinearity must be considered when calculating the stress-strain state (SSD) and vibrations of blades, thin compressor disks, structural elements of housings, and shafts and combustion chambers for stability. The article considers the possibility of using units of various configurations (i.e., wheeled, tracked, and walking). Motion systems have some disadvantages, including complexity and low reliability. One of the promising methods of moving mobile units, which has been developed in recent years at the Ilmenau University of Technology (Germany) and others, is a method based on the use of controlled vibrational movement of internal masses installed in the unit body. By changing the movement of the internal masses of a mobile vibrating unit, the reaction force of the external environment on the unit body can be controlled, ensuring its movement in the desired direction. Vibrating units are simple in design; they do not require special "drivers" such as wheels or tracks. This makes mobile vibrating units promising for movement not only on surfaces but also inside dense environments that impede penetration. In addition, a review of the design changes of the surfaces of the coke cone and fan blades, the use of noise-absorbing structures in the flow part of the gas turbine engine and in the elements of the protective coating of the structure, and the use of modernized combustion chambers with reduced NOx emissions was conducted.