Research Papers

Prediction of Aerodynamically Induced Blade Vibrations in a Radial Turbine Rotor Using the Nonlinear Harmonic Approach

[+] Author and Article Information
Nikola Kovachev

ITSM—Institute of Thermal Turbomachinery and
Machinery Laboratory,
University of Stuttgart,
Stuttgart 70569, Germany
e-mail: nikola.kovachev@itsm.uni-stuttgart.de

Christian U. Waldherr, Jürgen F. Mayer, Damian M. Vogt

ITSM—Institute of Thermal Turbomachinery and
Machinery Laboratory,
University of Stuttgart,
Stuttgart 70569, Germany

1Corresponding author.

Manuscript received June 25, 2018; final manuscript received July 6, 2018; published online September 21, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(2), 021007 (Sep 21, 2018) (10 pages) Paper No: GTP-18-1346; doi: 10.1115/1.4040856 History: Received June 25, 2018; Revised July 06, 2018

Resonant response of turbomachinery blades can lead to high cycle fatigue (HCF) if the vibration amplitudes are excessive. Accurate and reliable simulations of the forced response phenomenon require detailed CFD and FE models that may consume immense computational costs. In the present study, an alternative approach is applied, which incorporates nonlinear harmonic (NLH) CFD simulations in a one-way fluid–structure interaction (FSI) workflow for the prediction of the forced response phenomenon at reduced computational costs. Five resonance crossings excited by the stator in a radial inflow turbocharger turbine are investigated and the aerodynamic excitation and damping are predicted using this approach. Blade vibration amplitudes are obtained from a subsequent forced response analysis combining the aerodynamic excitation with aerodynamic damping and a detailed structural model of the investigated turbine rotor. A comparison with tip timing measurement data shows that all predicted values lay within the range of the mistuned blade response underlining the high quality of the utilized workflow.

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Fig. 3

CFD model of the investigated radial inflow turbine (only one sector shown)

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Fig. 2

Flow chart of the used one-way FSI approach

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Fig. 1

Schematic view of the positions of the unsteady pressure probes in the radial turbine

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Fig. 4

Campbell diagram for the BPF

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Fig. 5

Rotor blade mode shapes

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Fig. 11

Harmonic pressure amplitude distribution for M7

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Fig. 12

Harmonic blade loading at 40% span (left) and 95% span (right)

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Fig. 9

Convergence of the GF for two operating points

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Fig. 10

Streamlines at the rotor leading edge

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Fig. 6

Harmonic pressure amplitude

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Fig. 7

Harmonic pressure amplitude along the rotor shroud

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Fig. 8

Harmonic pressure amplitude at the BPF

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Fig. 13

GF from different numerical models

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Fig. 14

GF and absolute harmonic tangential force

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Fig. 15

Numerically predicted blade tip vibration amplitudes

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Fig. 16

Comparison with measured blade tip vibration amplitudes



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