0
research-article

Reduced Order Modeling for Multi-Stage Bladed Disks with Friction Contacts at the Flange Joint

[+] Author and Article Information
Giuseppe Battiato

DIMEAS, Politecnico di Torino, Torino, Italy
giuseppe.battiato@polito.it

Christian M. Firrone

DIMEAS, Politecnico di Torino, Torino, Italy
christian.firrone@polito.it

Teresa Berruti

DIMEAS, Politecnico di Torino, Torino, Italy
teresa.berruti@polito.it

Bogdan I. Epureanu

Department of Mechanical Engineering, University of Michigan, Ann Arbor, Michigan, USA
epureanu@umich.edu

1Corresponding author.

ASME doi:10.1115/1.4038348 History: Received July 04, 2017; Revised August 31, 2017

Abstract

Most aircraft turbojet engines consist of multiple stages coupled by means of bolted flange joints which potentially represent source of nonlinearities due to friction phenomena. Methods aimed at predicting the forced response of multi-stage bladed disks have to take into account such nonlinear behavior and its effect in damping blades vibration. In this paper a novel reduced order model is proposed for studying nonlinear vibration due to contacts in multi-stage bladed disks. The methodology exploits the shape of the single-stage normal modes at the inter-stage boundary being mathematically described by spatial Fourier coefficients. Most of the Fourier coefficients represent the dominant kinematics in terms of the well-known nodal diameters (standard harmonics), while the others, which are detectable at the inter-stage boundary, correspond to new spatial small wavelength phenomena named as extra harmonics. The number of Fourier coefficients describing the displacement field at the inter-stage boundary only depends on the specific engine order excitation acting on the multi-stage system. This reduced set of coefficients allows the reconstruction of the physical relative displacement field at the interface between stages and, under the hypothesis of the Single Harmonic Balance Method, the evaluation of the contact forces by employing the classic Jenkins contact element. The methodology is here applied to a simple multi-stage bladed disk and its performance is tested using as a benchmark the Craig-Bampton reduced order models of each single-stage. GT2017-64814

Copyright (c) 2017 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In