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Research Papers

Modeling the Microslip in the Flange Joint and Its Effect on the Dynamics of a Multistage Bladed Disk Assembly

[+] Author and Article Information
Christian M. Firrone

LAQ Aermec Laboratory,
Department of Mechanical
and Aerospace Engineering,
Politecnico di Torino,
Corso Duca degli Abruzzi 24,
Torino 10129, Italy
e-mail: christian.firrone@polito.it

Giuseppe Battiato

LAQ Aermec Laboratory,
Department of Mechanical
and Aerospace Engineering,
Politecnico di Torino,
Corso Duca degli Abruzzi 24,
Torino 10129, Italy
e-mail: 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, MI 48109-2125
e-mail: epureanu@umich.edu

1Corresponding author.

Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF COMPUTATIONAL AND NONLINEAR DYNAMICS. Manuscript received December 9, 2016; final manuscript received August 21, 2017; published online October 31, 2017. Assoc. Editor: Corina Sandu.

J. Comput. Nonlinear Dynam 13(1), 011011 (Oct 31, 2017) (10 pages) Paper No: CND-16-1614; doi: 10.1115/1.4037796 History: Received December 09, 2016; Revised August 21, 2017

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 multistage assemblies being computationally fast. In this paper, the flange joint connecting two turbine disks of a multistage 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 finite element model in order to calculate the nonlinear forced response.

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Figures

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Fig. 1

Multistage coupling between two stages at the interstage boundaries B1 and B2

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Fig. 2

Interstage boundary for a cyclic stage. Sectors and radial line segment are denoted with i and k, respectively.

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Fig. 3

Flow diagram for the multistage ROM generation

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Fig. 4

Simplified geometry of a rotor flange

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Fig. 5

Schematic model of a flange assembly: (a) undeformed geometry and (b) kinematics of the deformed geometry during vibration

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Fig. 6

Tangential contact forces at the contact interface

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Fig. 7

Tangential contact forces for the full stick and microslip case

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Fig. 8

Example of a fully stick (gray) and a microslip (black) hysteresis loop

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Fig. 9

HBM approximation of a hysteresis loop

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Fig. 10

Finite element representation of a flange: width b = 50 mm, thickness t = 10 mm, average radius rm = 300 mm

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Fig. 11

(a) contact displacements of the flange 1 and (b) tangential force on the flange 1

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Fig. 12

Flange 1, actual (bold) and HBM approximated tangential contact forces Sstiff and Sdamp

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Fig. 13

Example of one Jenkins contact element applied along the flange

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Fig. 14

Frequency response function for h = 2 excitation

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Fig. 15

Frequency response function for h = 5 excitation

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Fig. 16

Traveling response for h = 2 excitation (flange 1), f0 = 25 N, fres = 183 Hz. The circumferential length is discretized by 72 auxiliary master nodes.

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Fig. 17

Traveling response for h = 5 excitation (flange 1), f0 = 25 N, fres = 1430 Hz. The circumferential length is discretized by 72 auxiliary master nodes.

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