Research Papers: Gas Turbines: Structures and Dynamics

Effects of Contact Interface Parameters on Vibration of Turbine Bladed Disks With Underplatform Dampers

[+] Author and Article Information
C. W. Schwingshackl

 Imperial College London, London SW7 2AZ, UKc.schwingshackl@imperial.ac.uk

E. P. Petrov

 Imperial College London, London SW7 2AZ, UKy.petrov@imperial.ac.uk

D. J. Ewins

 Imperial College London, London SW7 2AZ, UKd.ewins@imperial.ac.uk

J. Eng. Gas Turbines Power 134(3), 032507 (Jan 09, 2012) (8 pages) doi:10.1115/1.4004721 History: Received May 03, 2011; Revised May 07, 2011; Published January 09, 2012; Online January 09, 2012

The design of high cycle fatigue resistant bladed disks requires the ability to predict the expected damping of the structure in order to evaluate the dynamic behavior and ensure structural integrity. Highly sophisticated software codes are available today for this nonlinear analysis, but their correct use requires a good understanding of the correct model generation and the input parameters involved to ensure a reliable prediction of the blade behavior. The aim of the work described in this paper is to determine the suitability of current modeling approaches and to enhance the quality of the nonlinear modeling of turbine blades with underplatform dampers. This includes an investigation of a choice of the required input parameters, an evaluation of their best use in nonlinear friction analysis, and an assessment of the sensitivity of the response to variations in these parameters. Part of the problem is that the input parameters come with varying degrees of uncertainty because some are experimentally determined, others are derived from analysis, and a final set are often based on estimates from previous experience. In this investigation the model of a commercial turbine bladed disk with an underplatform damper is studied, and its first flap, first torsion, and first edgewise modes are considered for 6 EO and 36 EO excitation. The influence of different contact interface meshes on the results is investigated, together with several distributions of the static normal contact loads, to enhance the model setup and, hence, increase accuracy in the response predictions of the blade with an underplatform damper. A parametric analysis is carried out on the friction contact parameters and the correct setup of the nonlinear contact model to determine their influence on the dynamic response and to define the required accuracy of the input parameters.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Scheme of the forced response analysis

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Figure 2

Generic friction model

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Figure 3

Friction parameter extraction from measured hysteresis loop

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Figure 4

The investigated turbine blade (a) and a schematic underplatform damper (b) with ten contact zones

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Figure 5

Investigated mesh configurations

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Figure 6

36 EO – Amplitude variation in % from the nominal model for various parameter changes

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Figure 7

36 EO – Frequency variation in % for various parameter changes

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Figure 8

36EO-1F: Amplitude response for kt  = kn variation

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Figure 9

6 and 36EO-1F: % Variation of amplitude from nominal for different parameters, kt and kn , μ, N0 , and mj

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Figure 10

6 and 36EO-1F: % Variation of amplitude and frequency from nominal for different number of elements

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Figure 11

36EO-1F: (a) Influence of element location on results and (b) the location of the nodes

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Figure 12

6EO-1F: (a) Influence of normal load distribution on amplitude and (b) the different distributions

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Figure 13

6EO-1F: influence of tangential and normal contact stiffness on amplitude response

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Figure 14

36EO-1F: Influence of included modes on amplitude



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