Session: 28-07 Dynamic Response of Bladed Disks

Paper Number: 123318

123318 - Development and Application of a High-Fidelity Numerical Tool for Dynamic Analysis of Bladed Disc Systems With Underplatform Dampers in Aircraft Engine Turbines 

This research aims to explore the mechanical behaviour of bladed disc systems with under-platform dampers in aircraft engine turbines through the development of a numerical tool. Utilising Abaqus and Python, the tool employs time-marching algorithms for high-fidelity time-domain simulations to calculate frequency domain behaviour. The CAD models used in this study are designed to be representative of actual turbine systems, thereby enhancing the validity and application of the research outcomes. One of the aspects of this tool is its capability to parallelise the calculations in many ways which softens the impact of the heavy computational load that is generated. Also, this tool can handle a large variety of systems that Abaqus can model since it uses Abaqus as its solver and thus, the solver is known to be efficient. This enables the numerical tool to account for the many sorts of nonlinearities, loads and conditions such as steady-state aero pressure and temperature distributions that influence the material’s elasticity. This multi-physical phenomenon, often cannot be fully integrated in conventional analyses, adds an additional layer of realism and complexity to the simulations. Harmonic excitation is applied to the system, and its response is monitored until a steady-state is reached. Within this steady-state, critical physical properties like damping amplitude are quantified and recorded. The measurement process is repeated across a selected frequency range that is of interest regarding the operational conditions of aircraft engines. Subsequently, a parametric study was conducted to investigate the effects of various design parameters. These parameters include normal loads exerted on the under-platform dampers and the stiffness of the contact area, both of which significantly impact the dynamic behaviour of the bladed disc system. The research goes beyond mere observation and interpretation; it provides a robust computational framework for systematically studying the effects of modifying design parameters on system behaviour. This not only expands the boundaries of computational modelling in mechanical and aerospace engineering but also serves as a cornerstone and a tool for validation for future studies and practical applications in aircraft engine design. The findings offer actionable insights that can substantially influence the design and manufacturing processes of next-generation aircraft engines, particularly concerning efficiency, safety, and reliability. Overall, this study displays a standardised tool that offers a flexible and reliable approach to understanding complex dynamical systems in the field of aerospace engineering. By developing a numerical tool and conducting an extensive parametric study, it delivers practical results that are directly applicable to the aerospace industry.

Presenting Author: Mertol Tüfekci University of Hertfordshire

Presenting Author Biography: Mertol TÜFEKCI graduated from Istanbul Technical University (ITU), Faculty of Mechanical Engineering with a BSc degree in 2016. He was a research assistant at the same institution. He was awarded with a scholarship from The Scientific and Technological Research Council of Turkey (TUBITAK) for his PhD study abroad. He completed his PhD at Imperial College London, Mechanical Engineering Department in 2022. Now he is a Lecturer at the University of Hertfordshire, Aerospace Engineering. He is mainly interested in programming mechanical problems and finite element analysis.

Authors:

Mertol Tüfekci University of Hertfordshire