Computational-and-Experimental Technique for Dynamic Characteristics Determining of the GTE Damping Supports with Elastic Rings

Aeronautical and Space-Rocket Engineering


Аuthors

Tereshko A. G.

e-mail: tereshko.ag@yandex.ru

Abstract

This article studies the development of a computational-and-experimental approach to determining the nonlinear stiffness and damping characteristics of the elastic-damping support for an aircraft gas turbine engine (GTE). The presented article considers the problem of creating a model of elastic-damping quasi-linear supports for the GTE rotors. This technique is intended for the cases of applying the support with elastic annular damper and nonlinear characteristics in the GTE structure, which parameters cannot be computed by classical analytical methods or with finite element modeling application. The problem is being solved by introduction of a quasi-linear element into a dynamic computational model created in the DYNAMICS R4 software package, which parameters change their value depending on the rotor speed. The values of the stiffness and damping coefficients were obtained by analyzing a large number of real engine starts and plotting experimental amplitude-frequency characteristics. Further, the unbalanced loads from the imbalance action are being added to the created computational model. The obtained unbalance response is being compared with the experimental amplitude-frequency characteristics of the rotor. The sections, in which the unbalance response of the dynamic model corresponded to the behavior of the real engine and the sections in which discrepancy presented, were being determined by the superposition of the computed and experimental graphs. The frequency range, in which a discrepancy between the computed and experimental data exists, will be considered as a mode with nonlinear characteristics of the support. The array of experimental points of the mode with nonlinear characteristics of the elastic-damping support is being divided into separate sections, for each of which it is possible to select a value of support rigidity, at which the unbalance response of the computed model will correspond to the experimental data within this section. The number of such sections was determined by the detail of the amplitude-frequency characteristics plotting and the total width of the frequency range, in which there a discrepancy between the computed and experimental data took place.
The proposed analysis of experimental data allows creating a quasi-linear model of the support that describes the dynamic behavior of the rotor, with account for the response to imbalances in the entire operating range of rotation frequencies. Application of the developed technique at the stage of engine development allows for the most accurate description of the system characteristics for predicting and further adjusting of the engine vibration state to ensure the vibration level required by regulatory documentation.

Keywords:

rotor dynamics, elastic-damping rotor support, model verification, DYNAMICS R4 software system

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