Research Papers: Gas Turbines: Structures and Dynamics

A Multiscale Approach for Nonlinear Dynamic Response Predictions With Fretting Wear

[+] Author and Article Information
J. Armand

Mechanical Engineering,
Imperial College London,
London SW7 2AZ, UK
e-mail: j.armand13@ic.ac.uk

L. Pesaresi, C. W. Schwingshackl

Mechanical Engineering,
Imperial College London,
London SW7 2AZ, UK

L. Salles

Mechanical Engineering,
Imperial College London,
London SW7 2AZ, UK

1Corresponding author.

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 20, 2016; final manuscript received June 28, 2016; published online September 13, 2016. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(2), 022505 (Sep 13, 2016) (7 pages) Paper No: GTP-16-1240; doi: 10.1115/1.4034344 History: Received June 20, 2016; Revised June 28, 2016

Accurate prediction of the vibration response of aircraft engine assemblies is of great importance when estimating both the performance and the lifetime of their individual components. In the case of underplatform dampers, for example, the motion at the frictional interfaces can lead to a highly nonlinear dynamic response and cause fretting wear at the contact. The latter will change the contact conditions of the interface and consequently impact the nonlinear dynamic response of the entire assembly. Accurate prediction of the nonlinear dynamic response over the lifetime of the assembly must include the impact of fretting wear. A multiscale approach that incorporates wear into the nonlinear dynamic analysis is proposed, and its viability is demonstrated for an underplatform damper system. The nonlinear dynamic response is calculated with a multiharmonic balance approach, and a newly developed semi-analytical contact solver is used to obtain the contact conditions at the blade–damper interface with high accuracy and low computational cost. The calculated contact conditions are used in combination with the energy wear approach to compute the fretting wear at the contact interface. The nonlinear dynamic model of the blade–damper system is then updated with the worn profile and its dynamic response is recomputed. A significant impact of fretting wear on the nonlinear dynamic behavior of the blade–damper system was observed, highlighting the sensitivity of the nonlinear dynamic response to changes at the contact interface. The computational speed and robustness of the adopted multiscale approach are demonstrated.

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Fig. 1

Scheme of the forced response analysis

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Fig. 2

Scheme of the AFT procedure

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Fig. 3

Scheme of the multiscale analysis

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Fig. 4

First out-of-phase flap mode of the two blades

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Fig. 5

Nonlinear contact element locations

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Fig. 6

Friction interface element

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Fig. 7

Initial pressure distribution

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Fig. 8

Frequency response function of the unworn system

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Fig. 9

Contact conditions at resonance

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Fig. 10

Normal and tangential force fields at resonance

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Fig. 11

Total moments at the center of the left contact patch

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Fig. 12

Total forces at the center of the left contact patch

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Fig. 13

Wear patterns after 500 (a) and 1000 (b) iterations

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Fig. 14

Impact of wear on pressure distribution

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Fig. 15

Impact of wear on the nonlinear FRF

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Fig. 16

Contact conditions at resonance with the worn profile

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Fig. 17

Evolution of the dissipated energy per cycle over time



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