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research-article

Modeling the Microslip in the Flange Joint and its Effect on the Dynamics of a Multi-Stage Bladed Disk Assembly

[+] Author and Article Information
Christian M. Firrone

Assistant Professor
christian.firrone@polito.it

Giuseppe Battiato

Ph.D. student, LAQ Aermec Laboratory, Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129, Torino, Italy
giuseppe.battiato@polito.it

Bogdan I. Epureanu

Professor, Applied Nonlinear Dynamics and Multi-Scale System Lab, Department of Mechanical Engineering, University of Michigan, Ann Arbor, Michigan, 48109-2125
epureanu@umich.edu

1Corresponding author.

ASME doi:10.1115/1.4037796 History: Received December 09, 2016; Revised August 21, 2017

Abstract

The complex architecture of aircraft engines requires demanding computational efforts when the dynamic coupling of their components has to be predicted. For this reason numerically efficient Reduced Order Models (ROM) have been developed with the aim of performing modal analyses and forced response computations on complex multi-stage assemblies being computationally fast. In this paper the flange joint connecting two turbine disks of a multi-stage assembly is studied as a source of nonlinearities due to friction damping occurring at the joint contact interface. An analytic contact model is proposed to calculate the local microslip based on the different deformations that the two flanges in contact take during vibration. The model is first introduced using a simple geometry representing two flanges in contact and then it is applied to a reduced FE model in order to calculate the nonlinear forced response.

Copyright (c) 2017 by ASME
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